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NATIONAL ADVISORY 
COMMITTEE FOR 
AERONAUTICS 



S80-W4U 



Rational * 23Q p 
iecoivautxcs) 



JL 



00/01 20022 



INDEX OF NACA TECHNICAL PUBLICATIONS 



June, 1955 - June, 1956 



^>X 








WASHINGTON - 1956 



PREFACE 

This Index of NACA Technical Publications covers those 
NACA research reports issued in the period of June 1955 
through June 1956. It is the fifth supplement to the basic 
1919-1949 Index. 

The research reports issued prior to June 1955 which 
have been declassified since that date have also been in- 
cluded. In addition, current announcement of newly declas- 
sified materials is regularly made in the NACA Research 
Abstracts and Reclassification Notice. 

The arrangement of the present Index follows that of its 
predecessors: (1) A listing of the subject categories by 
numerical classifications, (2) a chronological listing of the 
NACA research reports under each subject category, (3) an 
alphabetical index to the subject categories, and (4) an 
author index. An Explanatory Chart on page iii may be 
helpful in identifying references to NACA research reports 
encountered in the literature. 

Entries included herein duplicate in part the information 
of the index cards furnished with the individual research 
reports. Recipients maintaining card files may wish to 
discard those index cards on hand for unclassified research 
reports issued during the June 1955-June 1956 period. 

Newly available research reports are currently announced 
in the NACA Research Abstracts and Reclassification Notice 
and are normally available for a period of five years after 
announcement. Most of the older research reports (those 
issued prior to May 1951) are thus available on a "loan only M 
basis within the United States. Requests for NACA research 
reports should be forwarded to the address given below. 

Division of Research Information 

National Advisory Committee for Aeronautics 

1512 H Street, N. W. 

Washington 25, D. C. 

December 1, 1956 



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Subject 
Heading 
Number Subject Heading Outline 



1 


AERODYNAMICS 


1.1 


Fundamental Aerodynamics 


1.1.1 


Incompressible Flow 


1.1.2 


Compressible Flow 


1.1.2.1 


Subsonic Flow 


1.1.2.2 


Mixed Flow 


1.1.2.3 


Supersonic Flow 


1.1.3 


Viscous Flow 


1.1.3.1 


Laminar Flow 


1.1.3.2 


Turbulent Flow 


1.1.3.3 


Jet Mixing 


1.1.4 


Aerodynamics With Heat 


1.1.4.1 


Heating 


1.1.4.2 


Heat Transfer 


1.1.4.3 


Additions of Heat 


1.1.5 


Flow of Rarefied Gases 


1.1.5.1 


Slip Flow 


1.1.5.2 


Free Molecule Flow 


1.2 


Wings 


1.2.1 


Wing Sections 


1.2.1.1 


Section Theory 


1.2.1.2 


Section Variables 


1.2.1.2.1 


Camber 


1.2.1.2.2 


Thickness 


1.2.1.2.3 


Thickness Distribution 


1.2.1.2.4 


Inlets and Exits 


1.2.1.2.5 


Surface Conditions 


1.2.1.3 


Designated Profiles 


1.2.1.4 


High Lift Devices 


1.2.1.4.1 


Plain Flaps 


1.2.1.4.2 


Split Flaps 


1.2.1.4.3 


Slotted Flaps 


1.2.1.4.4 


Leading Edge Flaps 


1.2.1.4.5 


Slots and Slats 


1.4.1.5 


Controls 


1.1 1.5.1 


Flap Type 


1.2.1.5.2 


Spoilers 


1.2.1.6 


Boundary Layer 


1.2.1.6.1 


Characteristics 


1.2.1.6.2 


Control 


1.2.1.7 


Reynolds Number Effects 


1.2.1.8 


Mach Number Effects 


1.2.1.9 


Wake 


1.2.2 


Complete Wings 


1.2.2.1 


Wing Theory 


1.2.2.2 


Wing Variables 


1.2.2.2.1 


Profiles 


1.2.2.2.2 


Aspect Ratio 


1.2.2.2.3 


Sweep 


1.2.2.2.4 


Taper and Twist 


1.2.2.2.5 


Inlets and Exits 


1.2.2.2.6 


Surface Conditions 


1.2.2.2.7 


Dihedral 


1.2.2.3 


High Lift Devices 


1.2.2.3.1 


Trailing Edge Flaps 


1.2.2.3.2 


Slots and Slats 


1.2.2.3.3 


Leading Edge Flaps 


1.2.2.4 


Controls 


1.2.2.4.1 


Flap Type 


1.2.2.4.2 


Spoilers 


1.2.2.4.3 


All-Movable 


1.2.2.5 


Reynolds Number Effects 


1.2.2.6 


Mach Number Effects 


1.2.2.7 


Wake 


1.2.2.8 


Boundary Layer 


1.2.2.8.1 


Characteristics 


1.2.2.8.2 


Control 


1.3 


Bodies 


1.3.1 


Theory 



Page 

1-116 

2-15 

2 

3 

4-5 

5 

6-9 

9-10 

10-11 

11-13 

13 

13-14 

14 

14-15 

15 

15 

15 



16-50 
16 
16 
16 
16 

16-17 
17 

17 

17-18 



Subject 
Heading 
Number 



18 

18 

18 

18 

18 

19 

19 

19 

20 

20 

20-21 

21-22 

22-23 

23-25 

25-31 

31-32 

32 

32 

32-33 

33 

33-35 

35-36 

36 

36 

36-39 

39 

39-40 

40 

41-47 

47-49 

49 

49 

49-50 

51-57 
52-53 



1.3.2 

1.3.2.1 

1.3.2.2 

1.3.2.3 

1.3.2.4 

1.3.2.5 

1.3.3 

1.3.4 

1.3.4.1 

1.3.4.2 
1.3.4.3 
1.3.4.4 

1.3.5 

1.4 
1.4.1 
1.4.1.1 
1.4.1.1.1 



1.4.1.1.2 

1.4.1.1.3 

1.4.1.2 

1.4.1.3 

1.4.1.4 

1.4.1.4.1 

1.4.1,4.2 

1.4.2 

1.4.2.1 

1.4.2.1.1 

1.4.2.1.2 

1.4.2.2 

1.4.2.3 

1.4.2.4 

1.4.3 

1.4.4 

1.4.5 

1.4.5.1 

1.4.5.2 

1.4.6 

1.4.7 

1.4.7.1 

1.4.7.2 



1.5 

1.5.1 

1.5.2 

1.5.2.1 

1.5.2.2 
*1.5.2.3 
1.5.2.4 

1.5.2.5 
1.5.2.6 

1.5.2.7 

1.5.2.8 

1.5.2.9 
1.5.2.10 

1.5.3 

1.5.4 
1.5.5 

1.5.6 

1.5.7 



1.6 
1.6.1 
1.6.2 
1.6.2.1 
1.6.2.2 

1.7 

1.7.1 

1.7.1.1 



*No reports under this category for this period. 



Subject Heading Outline 

Shape Variables 

Fineness Ratio 

Cross Section 

Thickness Distribution 

Surface Conditions 

Protuberances 
Canopies 
Ducted Bodies 

Nose Shape 

Tail Shape 

Side Inlets 

Side Exits 
Hulls 

Internal Aerodynamics 
Air Inlets 
Nose, Central 
Propeller -Spinner-Cowl 

Combinations 
Subsonic 
Supersonic 
Nose, Annular 
Wing Leading Edge 
Side 
Scoops 
Submerged 
Ducts 
Diffusers 
Subsonic 
Supersonic 
Nozzles 
Pipes 
Bends 
Exits 

Jet Pumps and Thrust Augmentors 
Cascades 
Theory 
Experiment 
Fans 

Boundary Layer 
Characteristics 
Control 

Propellers 
Theory 
Design Variables 

Blade Sections 

Solidity 

Pitch Distribution 

Blade Plan Forms 

Mach Number Effects 

Pusher 

Dual Rotation 

Interference of Bodies 

Pitch and Yaw 

Diameter 
Designated Types 
Slipstream 
Selection Charts 
Operating Conditions 
Propeller -Spinner -Cowl 

Combinations 

Rotating Wings 
Theory 
Experimental Studies 

Power-Driven 

Autorotating 

Aircraft 
Airplanes 
Components in Combination 



Page 

53 

54 
54 
55 
55 

55-56 
56 
56 

56-57 

57 
57 



58-64 
58 
58 

58-59 
59 
59 
59 
59 
59 

59-60 
60 
60 

60-61 
61 
61 

61-62 
62 
62 
62 

62-63 
63 
63 

63-64 
64 
64 
64 
64 

65-67 
65 
65 
65 
65 



65 

65-66 
66 
66 

66-67 
67 

67 

67 



68 
68 
68 



69-88 

69 

69-70 



Subject 
Heading 
Number 



1.7.1.1.1 
1.7.1.1.2 
1.7.1.1.3 
1.7.1.1.4 
1.7.1.1.5 
1.7.1.2 
1.7.1.3 
1.7.2 
1.7.2.1 
1.7.2.1.1 
1.7.2.1.2 
1.7.2.1.3 
1.7.2.1.4 
1.7.2.2 
1.7.3 
1.7.3.1 
1.7.3.2 
*1.7.4 
♦1.7.4.1 
♦1.7.4.2 
*1.7.5 
1.7.6 

1.8 
1.8.1 
1.8.1.1 
1.8.1.1.1 
1.8.1.1.2 
1.8.1.1.3 
1.8.1.2 
1.8.1.2.1 
1.8.1.2.2 
1.8.1.2.3 
1.8.2 
1.8.2.1 
1.8.2.2 
1.8.2.3 
1.8.2.4 
1.8.2.5 
1.8.2.6 
1.8.3 
1.8.4 
1.8.5 
1.8.6 
*1.8.7 
1.8.8 

n.8.9 

1.9 

♦1.10 



2.1 

2.2 

2.3 
2.3.1 
2.3.2 
*2.3.3 

+2.3.4 
2.3.5 
2.3.6 

♦2.4 

♦2.5 
*2.5.1 



Subject Heading Outline 

Wing- Fuselage 
Wing-Nacelle 
Tail -Wing and Fuselage 
Propeller and Jet Interference 
External Stores 
Specific Airplanes 
Performance 
Missiles 
Components in Combination 
Wing-Body 
Tail-Body 
Jet Interference 
Wing-Taii-Body 
Specific Missiles 
Rotating-Wing Aircraft 
Autogiros 
Helicopters 
Seaplanes 
General Studies 
Specific Types 
Airships 
Biplanes and Triplanes 

Stability and Control 
Stability 
Static 

Longitudinal 
Lateral 
Directional 
Dynamic 
Longitudinal 
Lateral and Directional 
Damping Derivatives 
Control 
Longitudinal 
Lateral 
Directional 
Air Brakes 
Hinge Moments 
Automatic 
Spinning 
Stalling 

Flying Qualities 
Mass and Gyroscopic Problems 
Tumbling 

Automatic Stabilization 
Tracking 

Aeroelasticity 

Parachutes 



HYDRODYNAMICS 

Theory 

General Arrangement Studies 

Seaplane Hull Variables 
Length-Beam Ratio 
Dead Rise 
Steps 

Afterbody Shape 
Forebody Shape 
Chines 

Specific Seaplanes and Hulls 

Lateral Stabilizers 
Wing-Tip Float 



Page 

70-74 

74-75 

75-78 

79 

79-80 

80-82 

82-83 

83 

83-84 

84-85 

85-86 

86 

86 

86-87 

87 

87 

87-88 



88 

89-114 

89 

89 

89-96 

96-98 

98-99 

99 

99-100 

101-102 

102-103 

103 

104-106 

106-109 

109-110 

110 

110-111 

111 

112 

112 

112-113 

113-114 

114 



115-116 

117-123 

117 

118 

119 
119 
119 



119 
119 



Subject 
Heading 
Number 

2.6 

2.7 

2.8 

*2.9 

2.10 
*2.10.1 
*2.10.2 
*2. 10. 3 



3.1 

3.1.1 
♦3.1.1.1 
♦3.1.1.2 

♦3.1.2 

♦3.1.2.1 
♦3.1.2.2 
♦3.1.2.3 

3.1.3 

3.1.4 
♦3.1.5 

3.1.6 

3.1.7 

3.1.8 

3.1.9 

3.1.10 
♦3.1,11 
♦3.1.12 

3.2 

♦3.2.1 

♦3.2.1.1 
♦3.2.1.2 
♦3.2.1.3 

3.2.2 
♦3.2.3 

3.2.4 
♦3.2.5 
♦3.2.6 
♦3.2.7 
*3.2.8 

3.3 

♦3.3.1 
3.3.2 
3.3.2.: 
3.3.2.1 
3.3.2.1 

♦3.3.3 

3.4 
3.4.1 
3.4.2 
3.4.3 

♦3.4.3. 

♦3.4.3. 

♦3.4.3. 
3.4.3. 



Subject Heading Outline 

Planing Surfaces 

Hydrofoils 

Surface Craft 

Ditching Characteristics 

Stability and Control 
Longitudinal 
Lateral 
Directional 

PROPULSION 

Complete Systems 
Reciprocating Engines 

Spark-Ignition Engines 

Compression-Ignition (Diesel) 
Engines 
Reciprocating Engines - Turbines 

Turbosupercharged Engines 

Compound Engines 

Gas Generator - Turbine Engines 
Turbojet Engines 
Turbo-Propeller Engines 
Ducted Propeller Engines 
Pulse-Jet Engines 
Ram Jet Engines 
Rocket Engines 
Jet-Driven Rotors 
Nuclear Energy Systems 
Miscellaneous Engines 
Comparison of Engine Types 



Page 

120 
121 
122 

123 



125-154 

126-129 
126 



126-127 
127 

127 
128-129 
129 
129 
129 



1 

1.1 
1.2 
2 



3.4.3.3 



3.5 
3.5.1 



Control of Engines 
Charging and Control of 

Reciprocating Engines 

Spark-Ignition Engines 

Compression-Ignition Engines 

Compound Engines 
Control of Turbojet Engines 
Control of Turbine-Ram-Jet Engines 
Control of Turbine-Propeller Engines 
Control of Pulse-Jet Engines 
Control of Ram-Jet Engines 
Control of Rocket Engines 
Control of Gas Generator Engines 

Auxiliary Booster Systems 
Reciprocating Engines 
Gas Turbines 

Liquid Injection 

Afterburning 

Bleedoff 
Rocket Assist 

Fuels 
Preparation 

Physical and Chemical Properties 
Relation to Engine Performance 
Reciprocating Engines 
Spark -Ignition 

Compression-Ignition (Diesel) 
Turbine Engines, Ram Jets, 

and Pulse Jets 
Rockets (Includes Fuel and 
Oxidant) 

Combustion and Combustors 
General Combustion Research 



130 



130 
130 



131 

131 
131 
131 
131 



132-135 
132 

132-133 
133 



134 

134-135 

136-140 
136-137 



♦No reports under this category for this period. 



VI 



Subject 
Heading 
Number 

3.5.1.1 
3.5.1.2 
*3.5.1.3 
3.5.1.4 
3.5.1.5 
3.5.1.6 
3.5.2 



*3.5.2.1 
*3.5.2.1.1 
*3.5.2. 1.2 

3.5.2.2 

3.5.2.3 

*3.5.2.4 

3.5.2.5 

3.6 

3.6.1 

3.6.1.1 

3.6.1.2 

3.6.1.3 

*3.6.1.4 
3.6.2 

*3.6.3 

3.7 

3.7.1 

3.7.1.1 
*3. 7. 1.2 

3.7.1,3 

3,7.2 

3.7.3 
*3.7.4 

3.8 

3.8.1 

3.8.1.1 

3.8.1.2 

3.8.1.3 

3.8.2 

3.8.2.1 
*3.8.2.2 
*3.8.2. 3 
*3.8.2.4 
*3.8.S 
*3.8.3.1 

3.8.4 

3.8.4.1 

3.8.5 

3.9 

3.9.1 

3.9.1.1 

3.9.2 
*3.9.2. 1 
*3.9.2.2 
*3.9.2.3 

3.9.2.4 
*3.9.2.5 

3.10 
*3.10. 1 
*3.10.1.1 
*3.10. 1.2 

3.10.2 

3.10.3 
*3.10.4 
*3. 10. 5 



Subject Heading Outline 

Laminar-Flow Combustion 

Turbulent-Flow Combustion 

Detonation 

Effects of Fuel Atomization 

Reaction Mechanisms 

Ignition of Gases 
Effect of Engine Operating 

Conditions and Combustion 

Chamber Geometry 

Reciprocating Engines 
Spark-Ignition Engines 
Compression-Ignition (Diesel) 
Engines 

Turbine Engines 

Ram-Jet Engines 

Pulse-Jet Engines 

Rocket Engines 

Compression and Compressors 
Flow Theory and Experiment 

Axial Flow 

Radial Flow 

Mixed Flow 

Positive Displacement 
Stress and Vibration 
Matching 

Turbines 
Flow Theory and Experiment 

Axial Flow 

Radial Flow 

Mixed Flow 
Cooling 

Stress and Vibration 
Matching 

Friction and Lubrication 
Theory and Experiment 

Hydrodynamic Theory 

Chemistry of Lubrication 

Surface Conditions 
Sliding Contact Surfaces 

Sleeve Bearings 

Cylinder and Piston Mechanisms 

Slipper Plate 

Kingsbury and Mitchell Bearings 
Rolling Contact Surfaces 

Antifriction Bearings 
Sliding and Rolling Contact Surfaces 

Gears 
Lubricants 



Page 

137 
137 

137 
137 
138 



138 



138-139 
139-140 

140 

141-143 
141 

141-142 
142 

142-143 

143 



144-145 
144 
144 

144 

144-145 
145 



146-147 
146 
146 
146 
146 
146 
146 



146 
146 

147 



eat Transfer 


148-149 


Theory and Experiment 


148 


Cascades 


148 


Heat Exchangers 


149 


Radiators 




Intercoolers 




Aftercoolers 




Regenerators 


149 


Oil Coolers 





Cooling of Engines 
Reciprocating Engines 

Liquid -Cooled 

Air -Cooled 
Gas-Turbine Systems 
Ram Jets 
Pulse Jets 
Rockets 



150-151 



150-151 
151 



Subject 
Heading 
Number 

3.11.1 
3.11.2 

3.12 
3.12.1 
*3.12.1.1 
*3. 12. 1. 2 
*3.12.1.3 
3.12.1.4 
*3.12.1.5 
3.12.1.6 
3.12.1.7 
3.12.1.8 
3.12.2 
3.12.3 
*3.12.4 
*3.12.5 

3.13 



4.1 
4.1. 
4.1. 
4.1. 
4.1. 
4.1. 
4.1. 
4.1. 
4.1. 
4.1. 
4.1. 
4.1. 
4.1. 
4.1. 
4.1. 
4.1. 
►4.1. 



4.2 
4.2.1 
4.2.2 
4.2.2.1 
*4.2.2.2 
4.2.3 
4.2.4 
4.2.5 
4.2.6 



3. 11 Properties of Gases 

►No reports under this category for this period. 



152 



4.3 
4.3.1 
*4.3.1.1 
*4.3.1.2 
*4.3.1.3 
*4.3.2 
4.3.3 
4.3.3.1 
4.3.3.1.1 
4.3.3.1.2 
*4.3.3.2 
*4.3.3.2. 1 
*4.3.3.2.2 
4.3.4 
4.3.4.1 



Subject Heading Outline 

Kinetic 
Thermodynamic 

Accessories and Accessory Functions 
Fuel Systems 

Spark-Ignition Engines 

Compression -Ignition Engines 

Compound Engines 

Turbojet Engines 

Turbine -Propeller Engines 

Pulse-Jet Engines 

Ram -Jet Engines 

Rocket Engines 
Ignition Systems 
Starting Systems 
Lubrication Systems 
Cooling Systems 

Vibration and Flutter 



Page 

152 
152 

153 
153 



153 

153 
153 
153 
153 

153 



154 



1 
.1.1 
.1.1.1 
.1.1.2 
1.1.3 
1.1.4 
1.2 
1.2.1 
1.2.2 
1.2.3 
1.3 
1.4 
1.5 
2 

2.1 
2.1.1 
2.1.2 
2.2 
2.2.1 
2.2.2 
2.3 



AIRCRAFT LOADS AND 
CONSTRUCTION 

Loads 
Aerodynamic 
Wings 

Steady Loads 

Maneuvering 

Gust Loads 

Buffeting Loads 
Tail 

Steady Loads 

Maneuvering 

Buffeting and Gust 
Fuselage, Nacelles, and Canopies 
Rotating Wings 
Aeroelasticity 
Landing 
Impact 

Land 

Water 
Ground-Run 

Land 

Water 
Prelanding Conditions 

Vibration and Flutter 
Wings and Ailerons 
Tails 
Elevators and Rudders 
Tabs 
Bodies 

Propeller, Fans, and Compressors 
Rotating-Wing Aircraft 
Panels and Surface Coverings 



155-170 

155-162 

155 

155-156 

156-157 

157-158 

158 

158 

158-159 

159 

159 

159 

160 

160 

161 

161 

161 

161 

161-162 

162 

162 

162 



163-165 
164 
164 
164 

164-165 
165 
165 
165 



166 



Structures 
Columns 
Tubular 
Beams 
Sections 
Frames, Gridworks, and Trusses 
Plates 
Flat 
Unstiffened 

Stiffened iee 

Curved 
Unstiffened 
Stiffened 
Beams 
Box 



-170 
166 



166 
166 
166 
•167 



167 
167 



vii 



Subject 




Heading 




Number 


Subject Heading Outline 


*4.3.4.2 


Diagonal Tension 


4.3.5 


Shells 


4.3.5.1 


Cylinders 


4.3.5.1.1 


Circular 


M.S. 5. 1.2 


Elliptical 


4.3.5.2 


Boxes 


4.3.6 


Connections 


*4.3.6.1 


Bolted 


4.3.6.2 


Riveted 


4.3.6.3 


Welded 


4.3.6.4 


Bonded 


4.3.7 


Loads and Stresses 


4.3.7.1 


Tension 


4.3.7.2 


Compression 


4.3.7.3 


Bending 


4.3.7.4 


Torsion 


4.3.7.5 


Shear 


4.3.7.6 


Concentrated 


4.3.7.7 


Dynamic 


4.3.7.7.1 


Repeated 


4.3.7.7.2 


Transient 


*4.3.7.8 


Normal Pressures 


4.3.8 


Weight Analysis 


5 


MATERIALS 


5.1 


Types 


5.1.1 


Aluminum 


*5.1.2 


Magnesium 


5.1.3 


Steels 


5.1-4 


Heat-Resisting Alloys 


5.1.5 


Ceramics 


5.1.6 


Plastics 


*5.1.7 


Woods 


5.1.8 


Adhesives 


5.1.9 


Protective Coatings 


*5.1.10 


Fabrics 


*5.1.11 


Sandwich and Laminates 


5.1.12 


Ceramals 


5.2 


Properties 


5.2.1 


Tensile 


5.2.2 


Compressive 


5.2.3 


Creep 


5.2.4 


Stress -Rupture 


5.2.5 


Fatigue 


5.2.6 


Shear 


5.2.7 


Flexural 


5.2.8 


Corrosion Resistance 


5.2.9 


Structure 


5.2.10 


Effects of Nuclear Radiation 


5.2.11 


Thermal 


*5.2.12 


Multiaxial Stress 


5.2.13 


Plasticity 


5.3 


Operating Stresses and Conditions 


*5.3.1 


Airframe 


5.3.2 


Propulsion System 


6 


METEOROLOGY 


6.1 


Atmosphere 


6.1.1 


Standard Atmosphere 


6.1.2 


Gusts 


6.1.2.1 


Structure 


6.1-2.2 


Frequency 


6.1.2.3 


Turbulence 


6.1.2.4 


Alleviation 


*6.1.3 


Electricity 



Page 



167 
167 
167 

168 
168 

168 
168 
168 
168 
168 

168-169 
169 
169 
169 
169 

169-170 
170 
170 

170 



171-177 

172-173 
172 

172 
172 
173 
173 

173 
173 



173 

174-176 
174 



Subject 
Heading 
Number Subject Heading Outline 

6.2 Ice Formation 

7 OPERATING PROBLEMS 

7 i Safety 

7 i i Pilot-Escape Techniques 

7. 2 Navigation 

7 3 ice Prevention and Removal 

7* 3 i Engine Induction Systems 

7. 3. 2 Propellers 

7*3.3 Wings and Tails 

7.3.4 Windshields 

7 3 5 Miscellaneous Accessories 

7. 3. 6 propulsion Systems 

7.4 Noise 

*7. 5 Heating and Ventilating 

*7. e Lightning Hazards 

7. 7 Piloting Techniques 

7.8 Physiological 

7.9 Fire Hazards 

7. 10 General 

g INSTRUMENTS 

8. 1 Flight 

8.2 Laboratory 

8. 3 Meteorological 

9 RESEARCH EQUIPMENT AND 
TECHNIQUES 

Equipment 
Wind Tunnels 
Free-Flight 

Towing Tanks and Impact Basins 
Propulsion Research Equipment 
Propeller 
Materials 
Structures 

Technique 
Corrections 
Aerodynamics 
Hydrodynamics 
Loads and Construction 
Propulsion 
Operating Problems 
Mathematics 

NOMENCLATURE 

BIBLIOGRAPHIES AND INDEXES 

12 TECHNICAL SUMMARIES 



174 




175 


9.1 


175 


9.1.1 


175 


9.1.2 


175 


*9.1.3 


175 


9.1.4 


176 


*9.1.5 


176 


9.1.6 


176 


9.1.7 


176 


9.2 




9.2.1 


177 


9.2.2 




9.2.3 


177 


9.2.4 




9.2.5 




9.2.6 


>-182 


9.2.7 


180 




180 


*10 


180 




180 




180 


*11 


181 




181 





Page 
182 

183-191 

184 
184 

185 

186 
186 
186 
186 
186 
186 
186 

187 



188 
189 
190 
♦ 191 

193-196 
194 
195 
196 

197-204 

198 

198-199 

199 

200 

200 
200 

201-204 
201-202 
202 
203 
203 
204 
204 
204 



205 



*No reports under this category for this period. 



Vlll 




(1) 

AERODYNAMICS 



(1) AERODYNAMICS 



AERODYNAMICS 



REMARK ON THE THEORY OF LIFTING SUR- 
FACES. (Sulla teorla delle supertici portantl). 
Aldo Muggia. January 1956. lip. diagrs. 
(NACA TM 1386. Trans, from Attl delta Accademla 
delle Sclenze dl Torino, v. 87, 1952-1953) 



A FLAT WING WITH SHARP EDGES IN A SUPER- 
SONIC STREAM. A. E. Donov. March 1956. 48p. 
diagrs. (NACA TM 1394. Trans, from Akademlla 
NAUKSSSR, Izvestlla, 1939, p. 603-626) 



( 1 ) AERODYNAMICS 



Fundamental Aerodynamics 



PRELIMINARY INVESTIGATION OF EFFECTIVE- 
NESS OF BASE BLEED IN REDUCING DRAG OF 
BLUNT-BASE BODIES IN SUPERSONIC STREAM. 
Edgar M. Cortright. Jr., and Albert H. Schroeder. 
March 9, 1951. 23p. diagrs., photos. 
(NACA RM E51A26) 



A UNIFIED TWO-DIMENSIONAL APPROACH TO 
THE CALCULATION OF THREE-DIMENSIONAL 
HYPERSONIC FLOWS, WITH APPLICATION TO 
BODIES OF REVOLUTION. A. J. Eggers, Jr. and 
Raymond C. Savin. 1955. ii, 27p. diagrs., tab. 
(NACA Rept. 1249. Supersedes TN 2811) 



MAXIMUM THEOREMS AND REFLECTIONS OF 
SIMPLE WAVES. P. Germain, Brown University. 
June 1955. 22p. (NACA TN 3299) 



A FLAT WING WITH SHARP EDGES IN A SUPER- 
SONIC STREAM. A. E. Donov. March 1956. 48p. 
diagrs. (NACA TM 1394. Trans, from Akademiia 
NAUKSSSR, Izvestiia, 1939, p. 603-626) 



FORMATION OF A VORTEX AT THE EDGE OF A 
PLATE. (Ausbildung eines Wirbels an der Kante 
einer Platte). Leo Anton. March 1956. 36p. 
diagrs. (NACA TM 1398. Trans, from Ingenieur- 
Archiv, v. 10, 1939, p. 411-427) 



HEAT CAPACITY LAG OF GASEOUS MLXTURES. 
Thomas D. Rossing, Robert C. Amme, and Sam 
Legvold, Iowa State College. March 1956. 35p. 
diagrs., tabs. (NACA TN 3558) 



(l.U) 

INCOMPRESSIBLE FLOW 



RESULTS OF TWO FREE-FALL EXPERIMENTS ON 
FLUTTER OF THIN UNSWEPT WINGS IN THE 
TRANSONIC SPEED RANGE. William T. Lauten, Jr., 
and Herbert C. Nelson. May 8, 1951. 26p. diagrs., 
photo., tabs. (NACA RM L51C08) 



THE STRUCTURE OF TURBULENCE IN FULLY 
DEVELOPED PIPE FLOW. John Laufer, National 
Bureau of Standards. 1954. ii, 18p. diagrs. 
(NACA Rept. 1174. Formerly TN 2954) 



THE NORMAL COMPONENT OF THE INDUCED 
VELOCITY IN THE VICINITY OF A LIFTING ROTOR 
AND SOME EXAMPLES OF ITS APPLICATION. 
Walter Castles, Jr. and Jacob Henri De Leeuw, 
Georgia Institute of Technology. 1954. ii, 15p. 
diagrs., 3 tabs. (NACA Rept. 1184. Formerly 
TN 2912) 



IMPINGEMENT OF CLOUD DROPLETS ON A CYL- 
INDER AND PROCEDURE FOR MEASURING LIQUID- 
WATER CONTENT AND DROPLET SIZES IN SUPER- 
COOLED CLOUDS BY ROTATING MULTICYLINDER 
METHOD. R. J. Brun, W. Lewis, P. J. Perkins 
and J. S. Serafini. Appendix E: ALTERNATE 
METHOD OF REDUCING ROTATING MULTICYL- 
INDER DATA. Paul T. Hacker. 1955. iv, 43p. 
diagrs., photos., tabs. (NACA Rept. 1215. Super- 
sedes TN 2903; TN 2904; RM E53D23) 



THEORETICAL ANALYSIS OF INCOMPRESSIBLE 
FLOW THROUGH A RADIAL-INLET CENTRIFUGAL 
IMPELLER AT VARIOUS WEIGHT FLOWS. I - 
SOLUTION BY A MATRIX METHOD AND COMPAR- 
ISON WITH AN APPROXIMATE METHOD. Vasily D. 
Prian, James J. Kramer and Chung-Hua Wu. June 
1955. 39p. diagrs., tab. (NACA TN 3448) 



THEORETICAL ANALYSIS OF INCOMPRESSIBLE 
FLOW THROUGH A RADIAL-INLET CENTRIFUGAL 
IMPELLER AT VARIOUS WEIGHT FLOWS. U - 
SOLUTION IN LEADING-EDGE REGION BY RELAX- 
ATION METHODS. James J. Kramer. June 1955. 
19p. diagrs. (NACA TN 3449) 



REMARK ON THE THEORY OF LIFTING SUR- 
FACES. (Sulla teoria delle superfici portanti). 
Aldo Muggia. January 1956. lip. diagrs. 
(NACA TM 1386. Trans, from Atti della Accademia 
delle Scienze dl Torino, v. 87, 1952-1953) 



FORMATION OF A VORTEX AT THE EDGE OF A 
PLATE. (Ausbildung eines Wirbels an der Kante 
einer Platte). Leo Anton. March 1956. 36p. 
diagrs. (NACA TM 1398. Trans, from Ingenieur- 
Archiv, v. 10, 1939, p. 411-427) 



DETERMINATION OF VORTEX PATHS BY SERIES 
EXPANSION TECHNIQUE WITH APPLICATION TO 
CRUCIFORM WINGS. Alberta Y. Alksne. 
April 1956. 40p. diagrs., photos. (NACA TN 3670) 



NORMAL COMPONENT OF INDUCED VELOCITY IN 
THE VICINITY OF A LIFTING ROTOR WITH A NON- 
UNIFORM DISK LOADING. Harry H. Heyson and 
S. Katzoff. April 1956. i, 45p. diagrs. 
(NACA TN 3690) 



BOUNDARY LAYER. (Pogranichnyi sloi). 

L. G. Loitsianskii. May 1956. 29p. 

(NACA TM 1400. Trans, from Mechanics in the 

U.S.S.R. over Thirty Years, 1917-1947, p. 300-320) 



(1) AERODYNAMICS 



(U.2) 
COMPRESSIBLE FLOW 



RESULTS OF TWO FREE-FALL EXPERIMENTS ON 
FLUTTER OF THIN UNSWEPT WINGS IN THE 
TRANSONIC SPEED RANGE. William T. Lauten, Jr., 
and Herbert C. Nelson. May 8, 1951. 26p. diagrs., 
photo., tabs. (NACA RM L51C08) 



PRELIMINARY AIR- FLOW AND THRUST CALIBRA- 
TIONS OF SEVERAL CONICAL COOLING-AIR 
EJECTORS WITH A PRIMARY TO SECONDARY 
TEMPERATURE RATIO OF 1.0. I - DIAMETER 
RATIOS OF 1.21 AND 1.10. W. K. Greathouse and 
D. P. HoUister. July 1952. 24p. diagrs. 
(NACA RM E52E21) 



PRELIMINARY AIR- FLOW AND THRUST CALIBRA- 
TIONS OF SEVERAL CONICAL COOLING-AIR 
EJECTORS WITH A PRIMARY TO SECONDARY 
TEMPERATURE RATIO OF 1.0. H - DIAMETER 
RATIOS OF 1.06 AND 1.40. W. K. Greathouse and 
D. P. HoUister. August 1952. 35p. diagrs. 
(NACA RM K52F26) 



DEVELOPMENT OF TURBULENCE-MEASURING 
EQUIPMENT. Leslie S. G. Kovasznay, John 
Hopkins University. 1954. ii, 30p. diagrs., 
photos., tab. (NACA Rept. 1209. Supersedes 
TN 2839) 



A SUMMARY OF INFORMATION ON SUPPORT 
INTERFERENCE AT TRANSONIC AND SUPERSONIC 
SPEEDS. Eugene S. Love. January 1954. 26p. 
diagrs. (NACA RM L53K12) 



A CORRELATION BY MEANS OF TRANSONIC 
SIMILARITY RULES OF EXPERIMENTALLY DE- 
TERMINED CHARACTERISTICS OF A SERIES OF 
SYMMETRICAL AND CAMBERED WINGS OF 
RECTANGULAR PLAN FORM. John B. McDevitt. 
1955. ii, 23p. diagrs., tabs. (NACA Rept. 1253. 
Supersedes RM A51L17b; RM A53G31) 



ESTIMATION OF INLET LIP FORCES AT SUBSONIC 
AND SUPERSONIC SPEEDS. W. E. Moeckel. June 
1955. 12p. diagrs. (NACA TN 3457) 



RECOVERY AND TIME-RESPONSE CHARACTER- 
ISTICS OF SDC THERMOCOUPLE PROBES IN SUB- 
SONIC AND SUPERSONIC FLOW. Truman M. 
Stickney. July 1955. 25p. diagrs., photos., 2 tabs. 
(NACA TN 3455) 



PRELIMINARY PERFORMANCE DATA OF SEVERAL 
TAIL-PIPE-CASCADE-TYPE MODEL THRUST 
REVERSERS. James G. Henzel, Jr. and Jack G. 
McArdle. August 1955. 48p. diagrs., photos., tab. 
(NACA RM E55F09) 



MEASUREMENTS OF TURBULENT SKIN FRICTION 
ON A FLAT PLATE AT TRANSONIC SPEEDS. 
Raimo J(aakko) Hakkinen, California Institute of 
Technology. September 1955. 4 Ip. diagrs., photo- 
tabs. (NACA TN 3486) 



AVERAGING OF PERIODIC PRESSURE PULSA- 
TIONS BY A TOTAL-PRESSURE PROBE. R. C. 
Johnson. October 1955. 30p. diagrs., photo., 
tabs. (NACA TN 3568) 



SUMMARY OF RESULTS OBTAINED BY 
TRANSONIC -BUMP METHOD ON EFFECTS OF 
PLAN FORM AND THICKNESS ON LIFT AND DRAG 
CHARACTERISTICS OF WINGS AT TRANSONIC 
SPEEDS. Edward C. Polhamus. November 1955. 
33p. diagrs., tab. (NACA TN 3469. Supersedes 
RM L51H30) 



COMPRESSIBLE LAMINAR BOUNDARY LAYER 
AND HEAT TRANSFER FOR UNSTEADY MOTIONS 
OF A FLAT PLATE. Simon Ostrach. November 
1955. 26p. diagrs., tab. (NACA TN 3569) 



TURBULENT HEAT-TRANSFER MEASUREMENTS 
AT A MACH NUMBER OF 0.87. Maurice J. 
iirevoort and Bernard Kashis. December 1955. 
13p. diagrs. {NACA TN 3599) 



EFFECT OF TRANSVERSE BODY FORCE ON CHAN- 
NEL FLOW WITH SMALL HEAT ADDITION. Simon 
Ostrach and Franklin K. Moore. February 1956. 
31p. diagrs. (NACA TN 3594) 



ON THE GAS DYNAMICS OF A ROTATING IMPEL- 
LER. (Zur Gasdynamik des drehenden 
Schaufelsterns). A. Busemann. March 1956. 
16p. diagrs. (NACA TM 1385. Trans, from 
Zeitschrift fiir angewandte Mathematik und Mechanik, 
v. 18, no. 1, February 1938, p. 31-38) 



A FLAT WING WITH SHARP EDGES IN A SUPER- 
SONIC STREAM. A. E. Donov. March 1956. 48p. 
diagrs. (NACA TM 1394. Trans, from Akademiia 
NAUKSSSR, Izvestiia, 1939, p. 603-626) 



BOUNDARY-LAYER GROWTH AND SHOCK ATTEN- 
UATION IN A SHOCK TUBE WITH ROUGHNESS. 
Paul W. Huber and Donald R. McFarland. March 
1956. 49p. diagrs., photos., tab. (NACA TN 3627) 



DISCHARGE COEFFICIENTS FOR COMBUSTOR- 
LINER AIR-ENTRY HOLES. I - CIRCULAR HOLES 
WITH PARALLEL FLOW. Ralph T. Dittrich and 
Charles C. Graves. April 1956. 39p. diagrs. 
(NACA TN 3663) 



BOUNDARY LAYER. (Pogranichnyi sloi). 

L. G. Loitsianskii. May 1956. 29p. 

(NACA TM 1400. Trans, from Mechanics in the 

U.S.S.R. over Thirty Years, 1917-1947, p. 300-320) 



(1) AERODYNAMICS 



(1. 1.2. 1) 
SUBSONIC FLOW 



ANALYSIS AND EXPERIMENTAL OBSERVATION OF 
PRESSURE LOSSES IN RAM-JET COMBUSTION 
CHAMBERS. William H. Sterbentz. November 4, 
1949. 22p. diagrs. (NACA RM E9H19) 

PRESSURE MEASUREMENTS ON A BODY OF REVO- 
LUTION IN THE LANGLEY 16-FOOT TRANSONIC 
TUNNEL AND A COMPARISON WITH FREE-FALL 
DATA. Joseph M. Hallissy, Jr. March 1952. 19p. 
diagrs. (NACA RM L51L07a) 



TRANSONIC DRAG CHARACTERISTICS AND PRES- 
SURE DISTRIBUTION ON THE BODY OF A WING- 
BODY COMBINATION CONSISTING OF A BODY OF 
REVOLUTION OF FINENESS RATIO 12 AND A WING 
HAVING SWEEPBACK OF 45°, ASPECT RATIO 4, 
TAPER RATIO 0.6, AND NACA 65A006 AIRFOIL 
SECTIONS. Max C. Kurbjun and Jim Rogers 
Thompson. April 1952. 28p. diagrs., photo., tabs. 
(NACA RM L52B12) 



FREE-FALL MEASUREMENTS OF THE EFFECTS 
OF WING-BODY INTERFERENCE ON THE TRAN- 
SONIC DRAG CHARACTERISTICS OF SWEPT -WING - 
SLENDER-BODY CONFIGURATIONS. Max C. 
Kurbjun and Jim Rogers Thompson. May 1953. 34p. 
diagrs., photos., tabs. (NACA RM L53C31) 



FLOW DIFFUSION IN A CONSTANT-DIAMETER 
DUCT DOWNSTREAM OF AN ABRUPTLY TERMI- 
NATED CENTER BODY. Charles C. Wood and 
James T. Higginbotham. July 1953. 27p. diagrs. 
(NACA RM L53D23) 

ON THE DEVELOPMENT OF TURBULENT WAKES 
FROM VORTEX STREETS. Anatol Roshko, Cali- 
fornia Institute of Technology. 1954. ii, 25p. 
diagrs., photos., 3 tabs. (NACA Rept. 1191. 
Formerly TN 2913) 



THEORETICAL PERFORMANCE CHARACTERIS- 
TICS OF SHARP -LIP INLETS AT SUBSONIC 
SPEEDS. Evan A. Fradenburgh and DeMarquis D. 
Wyatt. 1954. ii, 8p. diagrs. (NACA Rept. 1193. 
Formerly TN 3004) 

PERFORMANCE AND BOUNDARY-LAYER DATA 
FROM 120 AND 23° CONICAL DIFFUSERS OF AREA 
RATIO 2.0 AT MACH NUMBERS UP TO CHOKING 
AND REYNOLDS NUMBERS UP TO 7.5 x 10 6 . 
B. H. Little, Jr., and Stafford W. Wilbur. 1954. 
ii, 23p. diagrs., tabs. (NACA Rept. 1201, Super- 
sedes RM L9H10; RM L9K10; RM L50C02a) 

EXPERIMENTAL INVESTIGATION OF THE OSCIL- 
LATING FORCES AND MOMENTS ON A TWO- 
DIMENSIONAL WING EQUIPPED WITH AN OSCIL- 
LATING CIRCULAR-ARC SPOILER. Sherman A. 
Clevenson and John E. Tomassoni. January 1954. 
20p. diagrs., photos. (NACA RM L53K18) 

PRELIMINARY INVESTIGATION OF THE FLOW IN 
AN ANNULAR-DIFFUSER— TAILPIPE COMBINA- 
TION WITH AN ABRUPT AREA EXPANSION AND 
SUCTION, INJECTION, AND VORTEX-GENERATOR 
FLOW CONTROLS. John R. Henry and Stafford W. 
Wilbur. February 1954. 27p. diagrs. 
(NACA RM L53K30) 



ON SLENDER-BODY THEORY AT TRANSONIC 
SPEEDS. Keith C. Harder and E. B. Klunker 
March 1954. 12p. (NACA RM L54A29a) 



IMPINGEMENT OF CLOUD DROPLETS ON A CYL- 
INDER AND PROCEDURE FOR MEASURING LIQUID- 
WATER CONTENT AND DROPLET SIZES IN SUPER- 
COOLED CLOUDS BY ROTATING MULTICYLINDER 
METHOD. R. J. Brun, W. Lewis, P. J. Perkins 
and J. S. Serafini. Appendix E: ALTERNATE 
METHOD OF REDUCING ROTATING MULTICYL- 
INDER DATA. Paul T. Hacker. 1955. iv, 43p. 
diagrs., photos., tabs. (NACA Rept 1215. Super- 
sedes TN 2903; TN 2904; RM E53D23) 



PRACTICAL CONSIDERATIONS IN SPECIFIC 
APPLICATIONS OF GAS-FLOW INTERFEROMETRY. 
Walton L. Howes and Donald R. Buchele. July 1955. 
ii, 95p. diagrs., photos. (NACA TN 3507) 



ACOUSTIC RADIATION FROM TWO-DIMENSIONAL 
RECTANGULAR CUTOUTS IN AERODYNAMIC 
SURFACES. K. Krishnamurty, California Institute 
of Technology. August 1955. 33p. diagrs., photos. 
(NACA TN 3487) 



SOME MEASUREMENTS GF FLOW INA RECTAN- 
GULAR CUTOUT. Anatol Roshko, California 
Institute of Technology. August 1955. 21p. diagrs. 
(NACA TN 3488) 



CONTRIBUTIONS ON THE MECHANICS OF 
BOUNDARY -LAYER TRANSITION. G. B. Schubauer 
and P. S. Klebanoff , National Bureau of Standards. 
September 1955. 31p. diagrs. (NACA TN 3489) 



VISUALIZATION STUDY OF SECONDARY FLOWS 
IN TURBINE ROTOR TIP REGIONS. Hubert W. 
Allen and Milton G. Kofskey. September 1955. 
33p. diagrs., photos., tab. (NACA TN 3519) 



FLIGHT INVESTIGATION OF THE SURFACE- 
PRESSURE DISTRIBUTION AND THE FLOW FIELD 
AROUND A CONICAL AND TWO SPHERICAL NON- 
ROTATING FULL-SCALE PROPELLER SPINNERS. 
Jerome B. Hammack, Milton L. Windier, and 
Elwood F. Scheithauer. September 1955. 36p. 
diagrs, , photos. (NACA TN 3535) 



INTENSITY, SCALE, AND SPECTRA OF TURBU- 
LENCE IN MDCING REGION OF FREE SUBSONIC 
JET. James C. Laurence. September 1955. 58p. 
diagrs., photo., tab. (NACA TN 3561) 



LAMINAR SEPARATION OVER A TRANSPIRATION- 
COOLED SURFACE IN COMPRESSIBLE FLOW. 
Morris Morduchow, Polytechnic Institute of Brook- 
lyn. December 1955. 32p. diagrs. 
(NACA TN 3559) 



ERROR IN AIRSPEED MEASUREMENT DUE TO 
THE STATIC -PRESSURE FIELD AHEAD OF AN 
AIRPLANE AT TRANSONIC SPEEDS. Thomas C. 
O'Bryan, Edward C. B. Danforth, and J. Ford 
Johnston. February 1956. 13p. diagrs., photos. 
(NACA Rept. 1239. Supersedes RM L9C25; 
RM L50L28; RM L52A17) 



(1) AERODYNAMICS 



DISCHARGE COEFFICIENTS FOR COMBUSTOR- 
LINER AIR-ENTRY HOLES. I - CIRCULAR HOLES 
WITH PARALLEL FLOW. Ralph T. Dittrich and 
Charles C. Graves. Aprii 1956. 39p. diagrs. 
(NACA TN 3663) 



EXPERIMENTAL MEASUREMENTS OF FORCES 
AND MOMENTS ON A TWO-DIMENSIONAL OSCIL- 
LATING WING AT SUBSONIC SPEEDS. Sherman A. 
Clevenson and Edward Widmayer, Jr. June 1956. 
28p. diagra., tab. (NACA TN 3686. Supersedes 
RM L9K28a) 



A STUDY OF THE HIGH-SPEED PERFORMANCE 
CHARACTERISTICS OF 90° BENDS IN CIRCULAR 
DUCTS. James T. Higginbotham, Charles C. Wood, 
and E. Floyd Valentine. June 1956. 28p. diagrs. 
(NACA TN 3696) 



(1. 1.2. 2) 
MIXED FLOW 



EFFECTS OF SWEEP ON CONTROLS. John G. 
Lowry, John A. Axelson, and Harold I. Johnson. 
June 3, 1948. 29p. diagrs. (NACA RM L8A28c) 



RESULTS OF TWO FREE-FALL EXPERIMENTS ON 
FLUTTER OF THIN UNSWEPT WINGS IN THE 
TRANSONIC SPEED RANGE. William T. Lauten, Jr., 
and Herbert C. Nelson. May 8, 1951. 26p. diagrs., 
photo., tabs. (NACA RM L51C08) 



PRESSURE MEASUREMENTS ON A BODY OF REVO- 
LUTION IN THE LANGLEY 16-FOOT TRANSONIC 
TUNNEL AND A COMPARISON WITH FREE-FALL 
DATA. Joseph M. Hallissy, Jr. March 1952. 19p. 
diagrs. (NACA RM L51L07a) 



TRANSONIC DRAG CHARACTERISTICS AND PRES- 
SURE DISTRIBUTION ON THE BODY OF A WING- 
BODY COMBINATION CONSISTING OF A BODY OF 
REVOLUTION OF FINENESS RATIO 12 AND A WING 
HAVING SWEEPBACK OF 45°, ASPECT RATIO 4, 
TAPER RATIO 0.6, AND NACA 65A006 AIRFOIL 
SECTIONS. Max C. Kurbjun and Jim Rogers 
Thompson. April 1952. 28p. diagrs., photo., tabs. 
(NACA RML52B12) 



PRESSURE DISTRIBUTION AND PRESSURE DRAG 
FOR A HEMISPHERICAL NOSE AT MACH NUM- 
BERS 2.05, 2.54. AND 3.04. Leo T. Chauvin. 
December 1952. 14p. diagrs., photos. 
(NACA RM L52K06) 



FREE-FALL MEASUREMENTS OF THE EFFECTS 
OF WING-BODY INTERFERENCE ON THE TRAN- 
SONIC DRAG CHARACTERISTICS OF SWEPT -WING- 
SLENDER-BODY CONFIGURATIONS. Max C. 
Kurbjun and Jim Rogers Thompson. May 1953. 34p. 
diagrs., photos., tabs. (NACA RM L53C31) 



EXPERIMENTAL CONVECTIVE HEAT TRANSFER 
TO A 4-INCH AND 6-INCH HEMISPHERE AT MACH 
NUMBERS FROM 1.62 TO 3.04. Leo T. Chauvin 
and Joseph P. Maloney. February 1954. 18p. 
diagrs., photos. (NACA RM L53L08a) 

ON SLENDER-BODY THEORY AT TRANSONIC 
SPEEDS. Keith C. Harder and E. B. Klunker. 
March 1954. 12p. (NACA RM L54A29a) 



MEASUREMENTS OF NORMAL-FORCE- 
COEFFICIENT FLUCTUATION ON FOUR 9- 
PERCENT-THICK AIRFOILS HAVING DIFFERENT 
LOCATIONS OF MAXIMUM THICKNESS. Milton D. 
Humphreys. April 1954. 21p. diagrs., photos. 
(NACA RM L54B22) 



THEORETICAL PREDICTION OF PRESSURE DIS- 
TRIBUTIONS ON NONLIFTING AIRFOILS AT HIGH 
SUBSONIC SPEEDS. John R. Spreiter and Alberta 
Alksne. 1955. iii, 42p. diagrs., photos. 
(NACA Rept. 1217. Supersedes TN 3096) 



MEASUREMENTS OF THE EFFECTS OF FINITE 
SPAN ON THE PRESSURE DISTRIBUTION OVER 
DOUBLE-WEDGE WINGS AT MACH NUMBERS 
NEAR SHOCK ATTACHMENT. Walter G. Vincenti. 
September 1955. 50p. diagrs. (NACA TN 3522) 

FLIGHT INVESTIGATION OF THE SURFACE- 
PRESSURE DISTRIBUTION AND THE FLOW FIELD 
AROUND A CONICAL AND TWO SPHERICAL NON- 
ROTATING FULL-SCALE PROPELLER SPINNERS. 
Jerome B. Hammack, Milton L. Windier, and 
Elwood F. Scheithauer. September 1955. 36p. 
diagrs. , photos. (NACA TN 3535) 



ERROR IN AIRSPEED MEASUREMENT DUE TO 
THE STATIC -PRESSURE FIELD AHEAD OF AN 
AIRPLANE AT TRANSONIC SPEEDS. Thomas C. 
O'Bryan, Edward C. B. Danforth, and J. Ford 
Johnston. February 1956. 13p. diagrs., photos. 
(NACA Rept. 1239. Supersedes RM L9C25; 
RM L50L28; RM L52A17) 



EFFECT OF THICKNESS, CAMBER, AND THICK- 
NESS DISTRIBUTION ON AIRFOIL CHARACTERIS- 
TICS AT MACH NUMBERS UP TO 1.0. Bernard N. 
Daley and Richard S. Dick. March 1956. 75p. 
diagrs., photos., tab. (NACA TN 3607. Supersedes 
RM L52G31a) 



EXPERIMENTAL INVESTIGATION OF THE FLOW 
AROUND LIFTING SYMMETRICAL DOUBLE- 
WEDGE AIRFOILS AT MACH NUMBERS OF 1.30 
AND 1.41. Faul B. Gooderum and George P. Wood. 
March 1956. 86p. diagrs., photos. 
(NACA TN 3626) 



ON THE RANGE OF APPLICABILITY OF THE 
TRANSONIC AREA RULE. John R. Spreiter. 
May 1956. 21p. diagrs. (NACA TN 3673. Super- 
sedes RM A54F28) 



THE FLOW PAST AN UNSWEPT- AND A SWEPT - 
WING-BODY COMBINATION AND THEIR EQUIVA- 
LENT BODIES OF REVOLUTION AT MACH NUM- 
BERS NEAR 1.0. Walter F. Lindsey. June 1956. 
18p. diagrs., photos. (NACA TN 3703. Supersedes 
RM L54A28a) 



(1) AERODYNAMICS 



(1. 1.2.3) 
SUPERSONIC FLOW 



EXPERIMENTAL INVESTIGATION AT SUPERSONIC 
SPEEDS OF TWIN-SCOOP DUCT INLETS OF EQUAL 
AREA. I. - AN INLET ENCLOSING 61.5 PERCENT 
OF THE MAXIMUM CIRCUMFERENCE OF THE 
FOREBODY. Wallace F. Davis and David L. 
Goldstein. January 21, 1948. 16p. diagrs., photos. 
(NACA RM A7J27) 



EXPERIMENTAL INVESTIGATION AT SUPERSONIC 
SPEEDS OF TWIN-SCOOP DUCT INLETS OF EQUAL 
AREA. O - EFFECTS OF SLOTS UPON AN INLET 
ENCLOSING 61.5 PERCENT OF THE MAXIMUM 
CIRCUMFERENCE OF THE FOREBODY. Wallace F. 
Davis and David L. Goldstein. June 9, 1948. 15p. 
diagrs., photos. (NACA RM A8C11) 



AERODYNAMIC INVESTIGATION OF A PARABOLIC 
BODY OF REVOLUTION AT MACH NUMBER OF 
1.92 AND SOME EFFECTS OF AN ANNULAR JET 
EXHAUSTING FROM THE BASE. Eugene S. Love. 
February 8, 1950. 75p. diagrs., photos., tab. 
(NACA RM L9K09) 



AERODYNAMIC CHARACTERISTICS OF NACA RM- 

10 MISSILE IN 8- BY 6-FOOT SUPERSONIC WIND 
TUNNEL AT MACH NUMBERS FROM 1.49 TO 1.98. 

11 - PRESENTATION AND ANALYSIS OF FORCE 
MEASUREMENTS. Fred T. Esenwein, Leonard J. 
Obery, and Carl F. Schueller. July 21, 1950. 34p 
diagrs., photo. (NACA RM E50D28) 



AERODYNAMIC CHARACTERISTICS OF NACA 
RM-10 MISSILE IN 8- BY 6-FOOT SUPERSONIC 
WIND TUNNEL AT MACH NUMBERS FROM 1.49 TO 
1.98. HI - ANALYSIS OF FORCE DISTRIBUTION 
AT ANGLE OF ATTACK (STABILIZING FINS RE- 
MOVED). Roger W. Luidens and Paul C. Simon. 
December 12, 1950. 26p. diagrs. 
(NACA RM E50I19) 



SOME EXPERIMENTS ON THE FLUTTER OF 
SWEPTBACK CANTILEVER WING MODELS AT 

MACH NUMBER 1.3. W. J. Tuovila. March 15, 
1951. lOp. diagrs., tab. (NACA RM L51A11) 



AN INVESTIGATION OF FOUR WINGS OF SQUARE 
PLAN FORM AT A MACH NUMBER OF 6.86 IN THE 
LANGLEY 11 -INCH HYPERSONIC TUNNEL. 
Charles H. McLellan, Mitchel H. Bertram, and 
JohnA. Moore. June 1951. 47p. diagrs., photos. 
(NACA RM L51D17) 



FLOW SEPARATION AHEAD OF A BLUNT AXIALLY 
SYMMETRIC BODY AT MACH NUMBERS 1.76 TO 
2.10. W. E. Moeckel. December 1951. 12p. 
diagrs., photos. (NACA RM E51I25) 



PRESSURE MEASUREMENTS ON A BODY OF REVO- 
LUTION IN THE LANGLEY 16-FOOT TRANSONIC 
TUNNEL AND A COMPARISON WITH FREE-FALL 
DATA. Joseph M. Hallissy, Jr. March 1952. 19p. 

diagrs. (NACA RM L51L07a) 



TRANSONIC DRAG CHARACTERISTICS AND PRES- 
SURE DISTRIBUTION ON THE BODY OF A WING- 
BODY COMBINATION CONSISTING OF A BODY OF 
REVOLUTION OF FINENESS RATIO 12 AND A WING 
HAVING SWEEPBACK OF 45°, ASPECT RATIO 4, 
TAPER RATIO 0.6, AND NACA 65A006 AIRFOIL 
SECTIONS, Max C. Kurbjun and Jim Rogers 
Thompson. April 1952. 28p. diagrs., photo., tabs. 
(NACA RML52B12) 



SOME WIND-TUNNEL RESULTS OF AN INVESTIGA- 
TION OF THE FLUTTER OF SWEPTBACK- AND 
TRIANGULAR-WING MODELS AT MACH NUMBER 
1.3. W. J. Tuovila. May 1952. 12p. diagrs., tab. 
(NACARM L52C13) 



PRELIMINARY DATA AT A MACH NUMBER OF 2.40 
OF THE CHARACTERISTICS OF FLAP-TYPE CON- 
TROLS EQUIPPED WITH PLAIN OVERHANG BAL- 
ANCES. James N. Mueller and K. R. Czarnecki. 
September 1952. 43p. diagrs., photos. 
(NACA RML52F10) 



INVESTIGATIONS AT SUPERSONIC SPEEDS OF THE 
BASE PRESSURE ON BODIES OF REVOLUTION * 
WITH AND WITHOUT SWEPTBACK STABILIZING 

FINS. Eugene S. Love and Robert M. O'Donnell. 
December 1952. 66p. diagrs., photos. 
(NACA RML52J21a) 



INVESTIGATION OF THE AERODYNAMIC CHARAC- 
TERISTICS OF THE NACA RM-10 MISSILE (WITH 
FINS) AT A MACH NUMBER OF 1.62 IN THE 
LANGLEY 9-INCH SUPERSONIC TUNNEL. Donald 
E. Coletti. December 1952. 21p. diagrs. 
(NACA RM L52J23a) 



PRESSURE DISTRIBUTION AND PRESSURE DRAG 
FOR A HEMISPHERICAL NOSE AT MACH NUM- 
BERS 2.05. 2.54. AND 3.04. Leo T. Chauvin. 
December 1952. 14p. diagrs., photos. 
(NACA RM L52K06) 



INVESTIGATIONS OF THE DAMPING IN ROLL OF 
SWEPT AND TAPERED WINGS AT SUPERSONIC 
SPEEDS. Russell W. McDearmon and Harry S. 
Heinke, Jr. March 1953. 35p. diagrs., photos., 
tab. (NACA RM L53A13) 



AN EXPERIMENTAL INVESTIGATION OF THE 
ZERO-LIFT-DRAG CHARACTERISTICS OF SYM- 
METRICAL BLUNT-TRAILING-EDGE AIRFOILS AT 
MACH NUMBERS FROM 2.7 TO 5.0. Clarence A. 
Syvertson and Hermilo R. Gloria. April 1953. 31p. 
diagrs., photos., tabs. (NACA RM A53B02) 



THE BASE PRESSURE AT SUPERSONIC SPEEDS 
ON TWO-DIMENSIONAL AIRFOILS AND BODIES OF 
REVOLUTION (WITH AND WITHOUT FINS) HAVING 
TURBULENT BOUNDARY LAYERS. Eugene S. Love. 
April 1953. 65p. diagrs., photos. (NACA 
RM L53C02) 

FREE-FALL MEASUREMENTS OF THE EFFECTS 
OF WING-BODY INTERFERENCE ON THE TRAN- 
SONIC DRAG CHARACTERISTICS OF SWEPT -WING- 
SLENDER-BODY CONFIGURATIONS. Max C. 
Kurbjun and Jim Rogers Thompson. May 1953. 34p. 
diagrs., photos., tabs. (NACA RM L53C31) 



(1) AERODYNAMICS 



SLOTTED-BOUNDARY INTERFERENCE EFFECTS 
ON WEDGE AIRFOILS AT LOW SUPERSONIC MACH 
NUMBERS. William J. Nelson and Allen R. Vick. 
July 1953. 27p. diagrs., photos. 
(NACA RML53F11) 



THEORY OF WING -BODY DRAG AT SUPERSONIC 
SPEEDS. Robert T. Jones. September 1953. lip. 
diagrs. (NACA RM A53H18a) 



INVESTIGATION OF REYNOLDS NUMBER EF- 
FECTS FOR A SERIES OF CONE-CYLINDER 
BODIES AT MACH NUMBERS OF 1.62, 1.93, AND 
2.41. Carl E. Grigsby and Edmund L. Ogburn. 
October 1953. 20p. diagrs., photos. (NACA 
RM L53H21) 



EFFECT OF VARIABLE VISCOSITY AND THERMAL 
CONDUCTIVITY ON HIGH-SPEED SLIP FLOW BE- 
TWEEN CONCENTRIC CYLINDERS. T. C. Lin and 
R. E. Street, University of Washington. 1954. ii, 
36p. diagrs. (NACA Rept. 1175. Formerly 
TN 2895) 



SUPERSONIC FLOW PAST OSCILLATING AIRFOILS 
INCLUDING NONLINEAR THICKNESS EFFECTS. 
Milton D. Van Dyke. 1954. ii, I7p, diagrs. (NACA 
Rept. 1183. Formerly TN 2982) 



A STUDY OF HYPERSONIC SMALL-DISTURBANCE 
THEORY. Milton D. Van Dyke. 1954. ii, 21p. 
diagrs. (NACA Rept. 1194. Formerly TN 3173) 



A SUMMARY OF INFORMATION ON SUPPORT 
INTERFERENCE AT TRANSONIC AND SUPERSONIC 
SPEEDS. Eugene S. Love. January 1954. 26p. 
diagrs. (NACA RM L53K12) 



EXPERIMENTAL CONNECTIVE HEAT TRANSFER 
TO A 4-INCH AND 6-INCH HEMISPHERE AT MACH 
NUMBERS FROM 1.62 TO 3.04. Leo T. Chauvin 
and Joseph P. Maloney. February 1954. 18p. 
diagrs., photos. (NACA RM L53L08a) 



AERODYNAMIC CHARACTERISTICS OF A CIRCU- 
LAR CYLINDER AT MACH NUMBER 6,86 AND 
ANGLES OF ATTACK UP TO 90°. Jim A. Penland. 
March 1954. 30p. diagrs., photos. 
(NACA RM L54A14) 



ON SLENDER-BODY THEORY AT TRANSONIC 
SPEEDS. Keith C. Harder and E. B. Klunker. 
March 1954. 12p. (NACA RM L54A29a) 



AN EXPERIMENTAL INVESTIGATION OF THE 
TRANSONIC- FLOW-GENERATION AND SHOCK- 
WAVE-REFLECTION CHARACTERISTICS OF A 
TWO-DIMENSIONAL WIND TUNNEL WITH 17- 
PERCENT-OPEN PERFORATED WALLS. Don D. 
Davis. Jr.. Thomas B. Sellers, and George M, Stokes. 
April 1954. 40p. diagrs., photos. 
{NACA RM L54B15a) 



DRAG AND HEAT TRANSFER ON A PARABOLIC 
BODY OF REVOLUTION (NACA RM-10) IN FREE 
FLIGHT TO MACH NUMBER 2 WITH BOTH CON- 
STANT AND VARYING REYNOLDS NUMBER AND 
HEATING EFFECTS ON TURBULENT SKIN FRIC- 
TION. Joseph P. Maloney. June 1954. 34p. 
diagrs,, photo. (NACA RM L54D06) 



AN INVESTIGATION OF THE CHARACTERISTICS OF 
THE NACA RM-10 (WITH AND WITHOUT FINS) IN 
THE LANGLEY 11-INCH HYPERSONIC TUNNEL AT 
A MACH NUMBER OF 6.9. William D. McCauley 
and William V. Feller. November 1954. 37p, 
diagrs., photos. (NACA RM L54I03) 



AN INVESTIGATION OF THE MAXIMUM LIFT OF 
WINGS AT SUPERSONIC SPEEDS. James J. 
Gallagher and James N. Mueller. 1955. ii, 28p. 
diagrs., photos., tabs. (NACA Rept. 1227. Super- 
sedes RM L7J10) 



SHOCK-TURBULENCE INTERACTION AND THE 
GENERATION OF NOISE. H. S. Ribner. 1955, 
iii, 19p. diagrs., tab. (NACA Rept. 1233. Super- 
sedes TN 3255) 



ARRANGEMENT OF FUSIFORM BODIES TO RE- 
DUCE THE WAVE DRAG AT SUPERSONIC SPEEDS. 
Morris D. Friedman and Doris Cohen. 1955. ii, 
8p. diagrs. (NACA Rept. 1236. Supersedes 
RM A51I20: TN 3345) 



A UNIFIED TWO-DIMENSIONAL APPROACH TO 
THE CALCULATION OF THREE-DIMENSIONAL 
HYPERSONIC FLOWS, WITH APPLICATION TO 
BODIES OF REVOLUTION. A. J. Eggers, Jr. and 
Raymond C. Savin. 1955. ii, 27p. diagrs., tab. 
(NACA Rept. 1249. Supersedes TN 2811) 



EXPLORATORY INVESTIGATION OF FLOW IN THE 
SEPARATED REGION AHEAD OF TWO BLUNT 
BODIES AT MACH NUMBER 2. Harry Bernstein 
and William E. Brunk. June 1955. 27p. diagrs., 
photos. (NACA RM E55D07b) 



TURBULENT -HEAT-TRANSFER MEASUREMENTS 
AT A MACH NUMBER OF 1.62. Maurice J. 
Brevoort and Bernard Rashis. June 1955. 15p. 
diagrs., tab. (NACA TN 3461) 



CALCULATION OF THE SUPERSONIC PRESSURE 
DISTRIBUTION ON A SINGLE-CURVED TAPERED 
WING IN REGIONS NOT INFLUENCED BY THE ROOT 
OR TIP. Walter G. Vincenti and Newman H. Fisher, 
Jr. June 1955. 32p. diagrs. (NACA TN 3499) 



A LOW-DENSITY WIND-TUNNEL STUDY OF 
SHOCK-WAVE STRUCTURE AND RELAXATION 
PHENOMENA IN GASES. F. S. Sherman, University 
of California. July 1955. 83p, diagrs., photos., 
2 tabs. (NACA TN 3298) 



AERODYNAMICS OF A RECTANGULAR WING OF 
INFINITE ASPECT RATIO AT HIGH ANGLES OF 
ATTACK AND SUPERSONIC SPEEDS. John C. 
Martin and Frank S. Malvestuto, Jr. July 1955. 
114p. diagrs., tab. (NACA TN 3421) 



(1) AERODYNAMICS 



THEORETICAL INVESTIGATION OF FLUTTER OF 
TWO-DIMENSIONAL FLAT PANELS WITH ONE 
SURFACE EXPOSED TO SUPERSONIC POTENTIAL 

FLOW. Herbert C. Nelson and Herbert J. 
Cunningham. July 1955. 60p. diagrs., tab. (NACA 
TN 3465) 



FLOW STUDIES ON FLAT-PLATE DELTA WINGS 
AT SUPERSONIC SPEED. William H. Michael, Jr. 
July 1955. 40p. diagrs., photos. (NACA TN 3472) 



PRACTICAL CONSIDERATIONS IN SPECIFIC 
APPLICATIONS OF GAS-FLOW INTERFEROMETRY. 
Walton L. Howes and Donald R. Buchele. July 1955. 
ii, 95p. diagrs., photos. (NACA TN 3507) 



A STUDY OF BOUNDARY-LAYER TRANSITION AND 
SURFACE TEMPERATURE DISTRIBUTIONS AT 
MACH3.12. Paul F. Brinich. July 1955. 39p. 
diagrs., photo. (NACA TN 3509) 



ON BOATTAIL BODIES OF REVOLUTION HAVING 
MINIMUM WAVE DRAG. Keith C. Harder and 
Conrad Rennemann, Jr. August 1955. 28p. diagrs., 
tab. (NACA TN 3478) 



ACOUSTIC RADIATION FROM TWO-DIMENSIONAL 
RECTANGULAR CUTOUTS IN AERODYNAMIC 
SURFACES. K. Krishnamurty, California Institute 
of Technology. August 1955. 33p. diagrs., photos. 
(NACA TN 3487) 



FLIGHT INVESTIGATION OF THE SURFACE- 
PRESSURE DISTRIBUTION AND THE FLOW FIELD 
AROUND A CONICAL AND TWO SPHERICAL NON- 
ROTATING FULL-SCALE PROPELLER SPINNERS. 
Jerome B. Hammack, Milton L. Windier, and 
Elwood F. Scheithauer. September 1955. 36p. 
diagrs. , photos. (NACA TN 3535) 



AN APPROXIMATE SOLUTION FOR AXIALLY 
SYMMETRIC FLOW OVER A CONE WITH AN AT- 
TACHED SHOCK WAVE. Richard A. Hord. 
October 1955. 32p. diagrs. (NACA TN 3485) 



THE PROPER COMBINATION OF LIFT LOADING 
FOR LEAST DRAG ON A SUPERSONIC WING. 
Frederick C. Grant. October 1955. 21p. diagrs. 
(NACA TN 3533) 



LAMINAR SEPARATION OVER A TRANSPIRATION- 
COOLED SURFACE IN COMPRESSIBLE FLOW. 
Morris Morduchow, Polytechnic Institute of Brook- 
lyn. December 1955. 32p. diagrs. 
(NACA TN 3559) 



PRESSURE RISE ASSOCIATED WITH SHOCK- 
INDUCED BOUNDARY-LAYER SEPARATION. 
Eugene S. Love. December 1955. 32p. diagrs. 
(NACA TN 3601) 



A SECOND-ORDER SHOCK-EXPANSION METHOD 
APPLICABLE TO BODIES OF REVOLUTION NEAR 
ZERO LIFT. Clarence A. Syvertson and David H. 
Dennis. January 1956. 57p. diagrs., tabs. 
(NACA TN 3527) 



INVESTIGATION OF THE EFFECT OF SHORT 
FLXED DIFFUSERS ON STARTING BLOWDOWN 
JETS IN THE MACH NUMBER RANGE FROM 2.7 
TO 4.5. John A. Moore. January 1956. 32p, 
diagrs., photos. (NACA TN 3545) 



DESIGN CRITERIA FOR AXISYMMETRIC AND TWO- 
DIMENSIONAL SUPERSONIC INLETS AND EXITS. 
James F. Connors and Rudolph C. Meyer. 
January 1956. 42p. diagrs., tabs. (NACA TN 3589) 



FLOW STUDIES ON DROOPED-LEADING-EDGE 
DELTA WINGS AT SUPERSONIC SPEED. William 
H. Michael, Jr. January 1956. 29p. diagrs., 
photos. (NACA TN 3614) 



MINIMUM WAVE DRAG FOR ARBITRARY AR- 
RANGEMENTS OF WINGS AND BODIES. Robert T. 
Jones. February 1956. lip. diagrs. 
(NACA TN 3530) 



TABULATION OF THE f x FUNCTIONS WHICH 
OCCUR IN THE AERODYNAMIC THEORY OF 
OSCILLATING WINGS IN SUPERSONIC FLOW. 
Vera Huckel. February 1956. 59p. tab. 
(NACA TN 3606) 



BODIES OF REVOLUTION HAVING MINIMUM DRAG 
AT HIGH SUPERSONIC AIRSPEEDS. A. J. Eggers, 
Jr., Meyer M. Resnikoff, and David H. Dennis. 
February 1956. 38p. diagrs., photos. 
(NACA TN 3666. Supersedes RM A51K27; A52D24) 



A FLAT WING WITH SHARP EDGES IN A SUPER- 
SONIC STREAM. A. E. Donov. March 1956. 48p. 
diagrs. (NACA TM 1394. Trans, from Akademiia 
NAUK SSSR, Izvestiia, 1939, p. 603-626) 



A METHOD FOR CALCULATING THE CONTOUR OF 
BODIES OF REVOLUTION WITH A PRESCRIBED 
PRESSURE GRADIENT AT SUPERSONIC SPEED 
WITH EXPERIMENTAL VERIFICATION. Paige B. 
Burbank. March 1956. 64p. diagrs., photos., 
tabs. (NACA TN 3555) 



LINEARIZED LIFTING-SURFACE AND LIFTING- 
LINE EVALUATIONS OF SIDEWASH BEHIND 
ROLLING TRIANGULAR WINGS AT SUPERSONIC 
SPEEDS. Percy J. Bobbitt. March 1956. 63p. 
diagrs. (NACA TN 3609) 



THEORETICAL ANALYSIS OF LINKED LEADING- 
EDGE AND TRAILING- EDGE FLAP-TYPE CON- 
TROLS AT SUPERSONIC SPEEDS. E. Carson 
Yates, Jr. March 1956. 4 Op. diagrs., tab. 
(NACA TN 3617) 



EXPERIMENTAL INVESTIGATION OF THE FLOW 
AROUND LIFTING SYMMETRICAL DOUBLE- 
WEDGE AIRFOILS AT MACH NUMBERS OF 1.30 
AND 1.41. Paul B. Gooderum and George P. Wood. 
March 1956. 86p. diagrs., photos. 
(NACA TN 3626) 



(1) AERODYNAMICS 



SOME EFFECTS OF BLUNTNESS ON BOUNDARY- 
LAYER TRANSITION AND HEAT TRANSFER AT 
SUPERSONIC SPEEDS. W. E. Moeckel. March 
1956. 43p. diagrs. (NACA TN 3653) 



EFFECT OF LEADING-EDGE GEOMETRY ON 
BOUNDARY-LAYER TRANSITION AT MACH 3.1. 
Paul F. Brinich. March 1956. 44p. diagrs., tabs. 

(NACA TN 3659) 



CALCULATIONS OF THE RATE OF THERMAL 
DISSOCIATION OF AIR BEHIND NORMAL SHOCK 
WAVES AT MACH NUMBERS OF 10, 12, AND 14. 
George P. Wood. April 1956. 4 Op. diagrs., tabs. 
(NACA TN 3634) 



FLAT PLATE CASCADES AT SUPERSONIC SPEED. 
(Ebene Plattengitter bei Uberschallgeschwindigkeit). 
Rashad M. El Badrawy. May 1956. iii, 130p. 
diagrs., photos., tabs. (NACA TM 1369. Trans, of 
Eidgenbssische Technische Hochschule Zurich. 
Institut fur Aerodynamik. Mitteilungen 19) 



EXPLORATORY INVESTIGATION OF BOUNDARY- 
LAYER TRANSITION ON A HOLLOW CYLINDER AT 
A MACH NUMBER OF 6.9. Mitchel H. Bertram. 
May 1956. 38p. diagrs., photo., tab. 
(NACA TN 3546) 



INVESTIGATION AT SUPERSONIC SPEEDS OF THE 
VARIATION WITH REYNOLDS NUMBER AND MACH 
NUMBER OF THE TOTAL, BASE, AND SKIN- 
FRICTION DRAG OF SEVEN BOATTAIL BODIES OF 
REVOLUTION DESIGNED FOR MINIMUM WAVE 
DRAG. August F. Bromm, Jr. and Julia M. 
Goodwin. June 1956. 20p. diagrs., photo. 
(NACA TN 3708. Supersedes RM L53l29b) 



THEORETICAL WAVE DRAG OF SHROUDED AIR- 
FOILS AND BODIES. Paul F. Byrd. June 1956. 
40p. diagrs. (NACA TN 3718) 



AN EVALUATION OF FOUR EXPERIMENTAL 
METHODS FOR MEASURING MEAN PROPERTIES 
OF A SUPERSONIC TURBULENT BOUNDARY 
LAYER. George J. Nothwang. June 1956. 34p. 
diagrs., photos. (NACA TN 3721) 



(1.1.3) 
VISCOUS FLOW 



CHARACTERISTICS OF FLOW OVER INCLINED 
BODIES OF REVOLUTION. H. Julian Allen and 
Edward W. Perkins. March 5, 1951. 47p. diagrs., 
photos. (NACA RM A50L07) 



AERODYNAMIC CHARACTERISTICS OF THE NACA 
RM-10 RESEARCH MISSILE IN THE AMES 1- BY 
3-FOOT SUPERSONIC WIND TUNNEL NO. 2 - 
PRESSURE AND FORCE MEASUREMENTS AT 
MACH NUMBERS OF 1.52 AND 1.98. Edward W. 
Perkins, Forrest E. Go wen and Leland H. Jorgensen. 
September 1951. 37p. diagrs. (NACA RM A51G13) 



FLOW SEPARATION AHEAD OF A BLUNT AXIALLY 
SYMMETRIC BODY AT MACH NUMBERS 1.76 TO 
2.10. W. E. Moeckel. December 1951. 12p. 
diagrs., photos. (NACA RM E51I25) 



PRELIMINARY DATA AT A MACH NUMBER OF 2.40 
OF THE CHARACTERISTICS OF FLAP-TYPE CON- 
TROLS EQUIPPED WITH PLAIN OVERHANG BAL- 
ANCES. James N. Mueller and K. R. Czarnecku 
September 1952. 43p. diagrs., photos. 
(NACA RML52F10) 



EFFECT OF VARIABLE VISCOSITY AND THERMAL 
CONDUCTIVITY ON HIGH-SPEED SLIP FLOW BE- 
TWEEN CONCENTRIC CYLINDERS. T. C. Lin and 
R. E. Street, University of Washington. 1954. ii, 
36p. diagrs. (NACA Rept. 1175. Formerly 
TN 2895) 



Kjn inr< ue* v aLj\jirvtlt,±> 



1 OF TTIRP.ITT.EM^ U/iVTT<3 



FROM VORTEX STREETS. Anatol Roshko, Cali- 
fornia Institute of Technology. 1954. ii, 25p. 
diagrs., photos., 3 tabs. (NACA Rept. 1191. 
Formerly TN 2913) 



AX EXPERIMENTAL INVESTIGATION OF THE 
TRANSONIC-FLOW-GENERATION AND SHOCK- 
WAVE-REFLECTION CHARACTERISTICS OF A 
TWO-DIMENSIONAL WIND TUNNEL WITH 17- 
PERCENT-OPEN PERFORATED WALLS, Don D. 
Davis. Jr., Thomas B. Sellers, and George M. Stokes. 
April 1954. 40p. diagrs., photos. 
(NACA RM L54Bl5a) 



DRAG MEASUREMENTS ON A 1/6-SCALE, FIN- 
LESS, STING-MOUNTED NACA RM-10 MISSILE IN 
FLIGHT AT MACH NUMBERS FROM 1.1 TO 4.04 
SHOWING SOME REYNOLDS NUMBER AND HEAT- 
ING EFFECTS. Robert O. Piland. October 1954. 
20p. diagrs., photos. (NACA RM L54H09) 



MEASUREMENTS OF TURBULENT SKIN FRICTION 
ON A FLAT PLATE AT TRANSONIC SPEEDS. 
Raimo J(aakko) Hakkinen, California Institute of 
Technology. September 1955. 41p. diagrs., photo, 
tabs. (NACA TN 3486) 



VISUALIZATION STUDY OF SECONDARY FLOWS 
IN TURBINE ROTOR TIP REGIONS. Hubert W. 
Allen and Milton G. Kofskey. September 1955, 
33p. diagrs., photos., tab, (NACA TN 3519) 



VARIATION OF BOUNDARY-LAYER TRANSITION 
WITH HEAT TRANSFER ON TWO BODIES OF 
REVOLUTION AT A MACH NUMBER OF 3.12. 
John R. Jack and N. S. Diaconis. September 1955. 
16p. diagrs., photos. (NACA TN 3562) 



10 



(1 ) AERODYNAMICS 



AVERAGING OF PERIODIC PRESSURE PULSA- 
TIONS BY A TOTAL-PRESSURE PROBE. R. C. 
Johnson. October 1955. 30p. diagrs., photo., 
tabs. (NACA TN 3568) 



BURNING VELOCITIES OF VARIOUS PREMIXED 
TURBULENT PROPANE FLAMES ON OPEN 
BURNERS. Paul Wagner. October 1955. 32p. 
diagrs., photos., tab. {NACA TN 3575) 



ON THE PERMEABILITY 07 POROUS MATERIALS. 
E. Carson Yates, Jr. January 1956. 31p. diagrs. 
(NACA TN 3596) 



CROSS FLOWS IN LAMINAR INCOMPRESSIBLE 
BOUNDARY LAYERS. Arthur G. Hansen and 
Howard Z. Herzig. February 1956. 50p. diagrs. , 
photos., tabs. (NACA TN 3651) 



FORMATION OF A VORTEX AT THE EDGE OF A 
PLATE. (Ausbildung eines Wirbels an der Kante 
einer Platte). Leo Anton. March 1956. 36p. 
diagrs. (NACA TM 1398. Trans, from Ingenieur- 
Archiv, v. 10, 1939, p. 411-427) 



A METHOD FOR CALCULATING THE CONTOUR OF 
BODIES OF REVOLUTION WITH A PRESCRIBED 
PRESSURE GRADIENT AT SUPERSONIC SPEED 
WITH EXPERIMENTAL VERIFICATION. Paige B. 
Burbank. March 1956. 64p. diagrs., photos., 
tabs. (NACA TN 3555) 



SOME EFFECTS OF BLUNTNESS ON BOUNDARY- 
LAYER TRANSITION AND HEAT TRANSFER AT 
SUPERSONIC SPEEDS. W. E. Moeckel. March 
1956. 43p. diagrs. (NACA TN 3653) 



EFFECT OF LEADING-EDGE GEOMETRY ON 
BOUNDARY -LAYER TRANSITION AT MACH 3.1. 
Paul F. Brinich. March 1956. 44p. diagrs., tabs. 
(NACA TN 3659) 



BOUNDARY LAYER. (Pogranichnyi sloi). 

L. G. Loitsianskii. May 1956. 29p. 

(NACA TM 1400. Trans, from Mechanics in the 

U.S.S.R. over Thirty Years, 1917-1947, p. 300-320) 



COMPARISON OF THE EXPERIMENTAL AND 
THEORETIOAL DISTRIBUTIONS OF LIFT ON A 
SLENDER INCLINED BODY OF REVOLUTION AT 
M = 2 1 - Edward W. Perkins and Donald M. Kuehn. 
May 1956. 39p. diagrs., photos., tabs. 
(NACA TN 3715. Supersedes RM A53E01) 



COMPARISON OF EXPERIMENTAL AND THEO- 
RETICAL NORMAL-FORCE DISTRIBUTIONS (IN- 
CLUDING REYNOLDS NUMBER EFFECTS) ON AN 
OGP/E- CYLINDER BODY AT MACH NUMBER 1.98. 
Edward W. Perkins and Leland H. Jorgensen. May 
1956. 50p. diagrs., tab. (NACA TN 3716. Super- 
sedes RM A54H23) 



PRELIMINARY REPORT ON A STUDY OF SEPA- 
RATED FLOWS IN SUPERSONIC AND SUBSONIC 
STREAMS. Dean R. Chapman, Donald M. Kuehn, 
and Howard K. Larson. June 1956. 15p. diagrs., 
photos. (NACA RM A55L14) 



SPACE HEATING RATES FOR SOME PREMIXED 
TURBULENT PROPANE-AIR FLAMES. Burton D. 
Fine and Paul Wagner. June 1956. 26p. diagrs., 
tab. (NACA TN 3277) 

APPLICATION OF SCATTERING THEORY TO THE 
MEASUREMENT OF TURBULENT DENSITY FLUC- 
TUATIONS BY AN OPTICAL METHOD. Howard A. 
Stine and Warren Winovich. June 1956. 21p. diagrs., 
(NACA TN 3719) 



(1. 1.3.1) 
LAMINAR FLOW 

AN INVESTIGATION OF FOUR WINGS OF SQUARE 
PLAN FORM AT A MACH NUMBER OF 6.86 IN THE 
LANGLEY 11 -INCH HYPERSONIC TUNNEL. 
Charles H. McLellan, Mitchel H. Bertram, and 
John A. Moore. June 1951. 47p. diagrs., photos. 
(NACA RM L51D17) 



INVESTIGATIONS AT SUPERSONIC SPEEDS OF THE 
BASE PRESSURE ON BODIES OF REVOLUTION 
WITH AND WITHOUT SWEPTBACK STABILIZING 

FINS. Eugene S. Love and Robert M. O'Donnell. 
December 1952. 66p. diagrs., photos. 
(NACA RM L52J2U) 



INVESTIGATION OF REYNOLDS NUMBER EF- 
FECTS FOR A SERIES OF CONE-CYLINDER 
BODIES AT MACH NUMBERS OF 1.62, 1.93, AND 
2.41. Cart E. Grigsby and Edmund L. Ogburn. 
October 1953. 20p. diagrs., photos. (NACA 
RM L53H21) 



AN INVESTIGATION OF THE CHARACTERISTICS OF 
THE NACA RM-10 (WITH AND WITHOUT FINS) IN 
THE LANGLEY 11-INCH HYPERSONIC TUNNEL AT 
A MACH NUMBER OF 6.9. William D. McCauley 
and William V. Feller. November 1954. 37p. 
diagrs., photos. (NACA RM L54I03) 



EXACT SOLUTIONS OF LAMINAR-BOUNDARY- 
LAYER EQUATIONS WITH CONSTANT PROPERTY 
VALUES FOR POROUS WALL WITH VARIABLE 
TEMPERATURE. Patrick L. Donoughe and John 
N. B. Livingood. 1955. ii, 21p. diagrs., tabs. 
(NACA Rept. 1229. Supersedes TN 3151) 



AN INVESTIGATION OF THE EFFECTS OF HEAT 
TRANSFER ON BOUNDARY- LAYER TRANSITION ON 
A PARABOLIC BODY OF REVOLUTION (NACA RM- 
10) AT A MACH NUMBER OF 1.61. K. R. Czarnecki 
and Archibald R. Sinclair. 1955. lip. diagrs., 
photos., tab. (NACA Rept. 1240. Supersedes 
TN 3165 and TN 3166) 



UNSTABLE CONVECTION IN VERTICAL CHANNELS 
WITH HEATING FROM BELOW, INCLUDING EF- 
FECTS OF HEAT SOURCES AND FRICTIONAL 
HEATING. Simon Ostrach. July 1955. 38p. diagrs., 
3 tabs. (NACA TN 3458) 



11 



(1) AERODYNAMICS 



PRACTICAL CONSIDERATIONS IN SPECIFIC 
APPLICATIONS OF GAS-FLOW INTERFEROMETRY. 
Walton L. Howes and Donald R. Buchele. July 1955. 
ii, 95p. diagrs., photos. (NACA TN 3507) 



LAMINAR FREE CONVECTION ON A VERTICAL 
PLATE WITH PRESCRIBED NONUNIFORM WALL 
HEAT FLUX OR PRESCRIBED NONUNIFORM WALL 
TEMPERATURE. E. M. Sparrow. July 1955. 34p. 
diagrs. (NACA TN 3508) 



A STUDY OF BOUNDARY-LAYER TRANSITION AND 
SURFACE TEMPERATURE DISTRIBUTIONS AT 
MACH 3.12. Paul F. Brinich. July 1955. 39p. 
diagrs., photo. (NACA TN 3509) 



HEAT TRANSFER AT THE FORWARD STAGNATION 
POINT OF BLUNT BODIES. Eli Reshotko and 
Clarence B. Cohen. July 1955. 17p. diagrs. 
(NACA TN 3513) 



CONTRIBUTIONS ON THE MECHANICS OF 
BOUNDARY-LAYER TRANSITION. G. B. Schubauer 
and P. S. Klebanoff, National Bureau of Standards. 
September 1955. 31p. diagrs. (NACA TN 3489) 



AN EXPERIMENTAL INVESTIGATION OF REGIONS 
OF SEPARATED LAMINAR FLOW. Donald E. 
Gault. September 1955. 65p. diagrs., photos., 4 tabs. 
(NACA TN 3505) 



COMPRESSIBLE LAMINAR BOUNDARY LAYER 
AND HEAT TRANSFER FOR UNSTEADY MOTIONS 
OF A FLAT PLATE. Simon Ostrach. November 
1955. 26p. diagrs., tab. (NACA TN 3569) 



LIFT HYSTERESIS AT STALL AS AN UNSTEADY 
BOUNDARY-LAYER PHENOMENON. Franklin K. 
Moore. November 1955. 32p. diagrs., tab. 
(NACA TN 3571) 



LAMINAR SEPARATION OVER A TRANSPIRATION - 
COOLED SURFACE IN COMPRESSIBLE FLOW. 
Morris Morduchow, Polytechnic Institute of Brook- 
lyn. December 1955. 32p. diagrs. 
(NACA TN 3559) 



SUMMARY OF LAMINAR-BOUNDARY -LAYER 
SOLUTIONS FOR WEDGE-TYPE FLOW OVER 
CONVECTION- AND TRANSPIRATION-COOLED 
SURFACES. John N. B. Livingood and Patrick L. 
Donoughe. December 1955. 33p. diagrs., tabs. 
(NACA TN 3588) 



PRESSURE RISE ASSOCIATED WITH SHOCK- 
INDUCED BOUNDARY -LAYER SEPARATION. 
Eugene S. Love. December 1955. 32p. diagrs. 
(NACA TN 3601) 



LAMINAR FLOW ABOUT A ROTATING BODY OF 

REVOLUTION IN AN AXIAL AIRSTREAM. (Die 
laminare Stromung urn einen axial angestromten 
rotierreden Drehkorper). H. Schlichting. 
(Abstract of paper presented at the Eighth Inter- 
national Mechanics Congress, Istanbul, August 
27, 1952). February 1956. 43p. diagrs., photo. 
(NACA TM 1415. Trans, from Ingenieur-Archiv, 
v. 21, no. 4, 1953, p. 227-244) 



CROSS FLOWS IN LAMINAR INCOMPRESSIBLE 
BOUNDARY LAYERS. Arthur G. Hansen and 
Howard Z. Herzig. February 1956. 50p. diagrs., 
photos., tabs. (NACA TN 3651) 



EXPLORATORY INVESTIGATION OF BOUNDARY- 
LAYER TRANSITION ON A HOLLOW CYLINDER AT 
A MACH NUMBER OF 6.9. Mitchel H. Bertram. 
May 1956. 38p. diagrs., photo., tab. 
(NACA TN 3546) 



INVESTIGATION OF BOUNDARY-LAYER TRANSI- 
TION ON 10° CONE IN LANGLEY 4- BY 4-FOOT 
SUPERSONIC PRESSURE TUNNEL AT MACH NUM- 
BERS OF 1.41, 1.61, AND 2.01. Archibald R. 
Sinclair and K. R. Czarnecki. May 1956. 17p. 
diagrs., photos. (NACA TN 3648) 



BOUNDARY LAYER BEHIND SHOCK OR THIN EX- 
PANSION WAVE MOVING INTO STATIONARY FLUI 



Harold Mirels. May 1956. 
(NACA TN 3712) 



i, 53p. diagrs., tabs. 



INVESTIGATION AT SUPERSONIC SPEEDS OF THE 
VARIATION WITH REYNOLDS NUMBER AND MACH 
NUMBER OF THE TOTAL, BASE, AND SKIN- 
FRICTION DRAG OF SEVEN BOATTAIL BODIES OF 
REVOLUTION DESIGNED FOR MINIMUM WAVE 
DRAG. August F. Bromm, Jr. and Julia M. 
Goodwin. June 1956. 20p. diagrs., photo. 
(NACA TN 3708. Supersedes RM L53I29b) 



(1.1.3.2) 
TURBULENT FLOW 



INVESTIGATIONS AT SUPERSONIC SPEEDS OF THE 
BASE PRESSURE ON BODIES OF REVOLUTION 
WITH AND WITHOUT SWEPTBACK STABILIZING 
FINS. Eugene S. Love and Robert M. O'Donnell. 
December 1952. 66p. diagrs., photos. 
(NACA RM L52J21a) 



THE BASE PRESSURE AT SUPERSONIC SPEEDS 
ON TWO-DIMENSIONAL AIRFOILS AND BODIES OF 
REVOLUTION (WITH AND WITHOUT FINS) HAVING 
TURBULENT BOUNDARY LAYERS. Eugene S. Love. 
April 1953. 65p. diagrs., photos. (NACA 
RM L53C02) 



FLOW DIFFUSION IN A CONSTANT-DIAMETER 
DUCT DOWNSTREAM OF AN ABRUPTLY TERMI- 
NATED CENTER BODY. Charles C. Wood and 
James T. Higginbotham. July 1953. 27p. diagrs. 
(NACA RM L53D23) 



12 



(1) AERODYNAMICS 



INVESTIGATION OF REYNOLDS NUMBER EF- 
FECTS FOR A SERIES OF CONE-CYLINDER 
BODIES AT MACH NUMBERS OF 1.62, 1.93, AND 
2.41. Carl E. Grigsby and Edmund L. Ogburn. 
October 1953. 20p. diagrs., photos. (NACA 
RM L53H21) 



THE STRUCTURE OF TURBULENCE IN FULLY 
DEVELOPED PIPE FLOW. John Laufer, National 
Bureau of Standards. 1954. 11, 18p. diagrs. 
(NACA Rept. 1174. Formerly TN 2954) 



PERFORMANCE AND BOUNDARY-LAYER DATA 
FROM 120 AND 23° CONICAL DIFFUSERS OF AREA 
RATIO 2.0 AT MACH NUMBERS UP TO CHOKING 
AND REYNOLDS NUMBERS UP TO 7.5 x 10 6 . 
B. H. Little, Jr., and Stafford W. Wilbur. 1954. 
ii, 23p. diagrs., tabs. (NACA Rept. 1201. Super- 
sedes RM L9H10; RM L9K10; RM L50C02a) 



PRELIMINARY INVESTIGATION OF THE FLOW IN 
AN ANNULAR-DIFFUSER — TAILPIPE COMBINA- 
TION WITH AN ABRUPT AREA EXPANSION AND 
SUCTION, INJECTION, AND VORTEX-GENERATOR 
FLOW CONTROLS. John R. Henry and Stafford W. 
Wilbur. February 1954. 27p. diagrs. 
(NACA RM L53K30) 



SOME OBSERVATIONS OF SHOCK-INDUCED TUR- 
BULENT SEPARATION ON SUPERSONIC DIF- 
FUSERS. T. J. Nussdorfer. May 1954. 14p. 
diagrs., photos. (NACA RM E51L26) 



DRAG AND HEAT TRANSFER ON A PARABOLIC 
BODY OF REVOLUTION (NACA RM-10) IN FREE 
FLIGHT TO MACH NUMBER 2 WITH BOTH CON- 
STANT AND VARYING REYNOLDS NUMBER AND 
HEATING EFFECTS ON TURBULENT SKIN FRIC- 
TION. Joseph P. Maloney. June 1954. 34p. 
diagrs., photo. (NACA RM L54D06) 



ANALYSIS OF TURBULENT HEAT TRANSFER, 
MASS TRANSFER, AND FRICTION IN SMOOTH 
TUBES AT HIGH PRANDTL AND SCHMIDT NUM- 
BERS. Robert G. Deissler. 1955. ii, 14p. 
diagrs. (NACA Rept. 1210. Supersedes TN 3145) 



SHOCK-TURBULENCE INTERACTION AND THE 
GENERATION OF NOISE. H. S. Ribner. 1955. 
iii, I9p. diagrs., tab. (NACA Rept. 1233. Super- 
sedes TN 3255) 



AN INVESTIGATION OF THE EFFECTS OF HEAT 
TRANSFER ON BOUNDARY -LAYER TRANSITION ON 
A PARABOLIC BODY OF REVOLUTION {NACA RM- 
10) AT A MACH NUMBER OF 1.61. K. R. Czarnecki 
and Archibald R. Sinclair. 1955. lip. diagrs., 
photos., tab. {NACA Rept. 1240. Supersedes 
TN 3165 andTN 3166) 



EXPLORATORY INVESTIGATION OF FLOW IN THE 
SEPARATED REGION AHEAD OF TWO BLUNT 
BODIES AT MACH NUMBER 2. Harry Bernstein 
and William E. Brunk. June 1955. 27p. diagrs., 
photos. (NACA RM E55D07b) 



TURBULENT-HEAT-TRANSFER MEASUREMENTS 
AT A MACH NUMBER OF 1.62. Maurice J. 
Brevoort and Bernard Rashis. June 1955. 15p. 
diagrs., tab. (NACA TN 3461) 



PROPAGATION OF A FREE FLAME IN A TURBU- 
LENT GAS STREAM. William R. Mickelsen and 
Norman E. Ernstein. July 1955. 89p. diagrs., 
photos., 2 tabs. (NACA TN 3456) 



A STUDY OF BOUNDARY -LAYER TRANSITION AND 
SURFACE TEMPERATURE DISTRIBUTIONS AT 
MACH 3.12. Paul F. Brinich. July 1955. 39p. 
diagrs., photo. (NACA TN 3509) 



SOME MEASUREMENTS OF FLOW IN A RECTAN- 
GULAR CUTOUT. Anatol Roshko, California 
Institute of Technology. August 1955. 21p. diagrs. 
(NACA TN 3488) 



CONTRIBUTIONS ON THE MECHANICS OF 
BOUNDARY-LAYER TRANSITION. G. B. Schubauer 
and P. S. Klebanoff, National Bureau of Standards. 
September 1955. 31p. diagrs. (NACA TN 3489) 



AN EXPERIMENTAL INVESTIGATION OF REGIONS 
OF SEPARATED LAMINAR FLOW. Donald E. 
Gault. September 1955. 65p. diagrs., photos., 4 tabs. 
(NACA TN 3505) 



FLIGHT INVESTIGATION OF THE SURFACE- 
PRESSURE DISTRIBUTION AND THE FLOW FIELD 
AROUND A CONICAL AND TWO SPHERICAL NON- 
ROTATING FULL-SCALE PROPELLER SPINNERS. 
Jerome B. Hammack, Milton L. Windier, and 
Elwood F. Scheithauer. September 1955. 36p. 
diagrs. , . photos. (NACA TN 3535) 



INTENSITY, SCALE, AND SPECTRA OF TURBU- 
LENCE IN MDCING REGION OF FREE SUBSONIC 

JET. James C. Laurence. September 1955. 58p. 
diagrs., photo., tab. (NACA TN 3561) 



THE THEORIES OF TURBULENCE. (Les Theories 
de la Turbulence). L. Agostini and J. Bass. 
October 1955. lC3p. diagrs. (NACA TM 1377. 
Trans, from Ministerc de l'Air, Publications 
Scientifiques et Techniques 2°7, 1-950) 



AN EXPERIMENTAL COMPARISON OF THE 
LAGRANGIAN AND EULERIAN CORRELATION 
COEFFICIENTS IN HOMOGENEOUS ISOTROPIC 
TURBULENCE. William R. Mickelsen. October 
1955. 42p. diagrs. (NACA TN 3570) 



13 



(1 ) AERODYNAMICS 



BURNING VELOCITIES OF VARIOUS PREMDCED 
TURBULENT PROPANE FLAMES ON OPEN 
BURNERS. Paul Wagner. October 1955. 32p. 
diagrs., photos., tab. (NACA TN 3575) 



CHARTS OF BOUNDARY-LAYER MASS FLOW AND 
MOMENTUM FOR INLET PERFORMANCE ANALY- 
SIS MACH NUMBER RANGE, 0.2 TO 5.0. Paul C. 
Simon and Kenneth L. Kowalski. November 1955. 
32p. diagrs., tab. (NACA TN 3583) 



TURBULENT HEAT-TRANSFER MEASUREMENTS 
AT A MACH NUMBER OF 0.87. Maurice J. 
Brevoort and Bernard Rashis. December 1955. 
13p. diagrs. (NACA TN 3599) 



PRESSURE RISE ASSOCIATED WITH SHOCK- 
INDUCED BOUNDARY-LAYER SEPARATION. 
Eugene S. Love. December 1955. 32p. diagrs. 
(NACA TN 3601) 



BOUNDARY-LAYER GROWTH AND SHOCK ATTEN- 
UATION IN A SHOCK TUBE WITH ROUGHNESS. 
Paul W. Huber and Donald R. McFarland. March 
1958. 49p. diagrs., photos., tab. (NACA TN 3627) 



EXPLORATORY INVESTIGATION OF BOUNDARY- 
LAYER TRANSITION ON A HOLLOW CYLINDER AT 
A MACH NUMBER OF 6.9. Mitchel H. Bertram. 
May 1956. 38p. diagrs., photo., tab. 
(NACA TN 3546) 



BOUNDARY LAYER BEHIND SHOCK OR THIN EX- 
PANSION WAVE MOVING INTO STATIONARY FLUID. 
Harold Mirels. May 1956. i, 53p. diagrs., tabs. 
(NACA TN3712) 



SPACE HEATING RATES FOR SOME PREMIXED 
TURBULENT PROPANE-AIR FLAMES. Burton D. 
Fine and Paul Wagner. June 1956. 26p. diagrs., 
tab. (NACA TN 3277) 



A STUDY OF THE HIGH-SPEED PERFORMANCE 
CHARACTERISTICS OF 90° BENDS IN CIRCULAR 
DUCTS. James T. Higginbotham, Charles C. Wood, 
and E. Floyd Valentine. June 1956. 28p. diagrs. 
(NACA TN 3696) 



APPLICATION OF SCATTERING THEORY TO THE 
MEASUREMENT OF TURBULENT DENSITY FLUC- 
TUATIONS BY AN OPTICAL METHOD. Howard A. 

Stlne and Warren Winovich. June 1956. 21p. diagrs., 
(NACA TN 3719) 



AN EVALUATION OF FOUR EXPERIMENTAL 
METHODS FOR MEASURING MEAN PROPERTIES 
OF A SUPERSONIC TURBULENT BOUNDARY 
LAYER. George J. Nothwang. June 1956. 34p. 
diagrs., photos. (NACA TN 3721) 



(1. 1.3.3) 
JET MIXING 



AERODYNAMIC INVESTIGATION OF A PARABOLIC 
BODY OF REVOLUTION AT MACH NUMBER OF 
1.92 AND SOME EFFECTS OF AN ANNULAR JET 
EXHAUSTING FROM THE BASE. Eugene S. Love. 
February 8, 1950. 75p. diagrs., photos., tab, 
(NACA RML9K09) 



INVESTIGATION AT MACH NUMBER 1.91 OF 
SPREADING CHARACTERISTICS OF JET EXPAND- 
ING FROM CHOKED NOZZLES. Morris D, Rousso 
and L. Eugene Baughman. February 1952. 27p. 
photos., diagrs. (NACA RM E51L19) 



PRELIMINARY DATA ON RAIN DEFLECTION FROM 
AffiCRAFT WINDSHIELDS BY MEANS OF HIGH- 
VELOCITY JET-AIR BLAST. Robert S. Ruggeri. 
July 1955. 17p. diagrs., photos. (NACA 
RM E55E17a) 



INTENSITY, SCALE, AND SPECTRA OF TURBU- 
LENCE IN MDCING REGION OF FREE SUBSONIC 
JET. James C. Laurence. September 4955. -58p. 
diagrs., photo., tab. (NACA TN 3561) 



EFFECT OF EXHAUST-NOZZLE EJECTORS ON 
TURBOJET NOISE GENERATION. Warren J. North 
and Willard D. Coles. October 1955. 26p. diagrs., 
photo. {NACA TN 3573) 



INVESTIGATION OF FAR NOISE FIELD OF JETS. 
I - EFFECT OF NOZZLE SHAPE. Edmund E. 
Callaghan and Willard D. Coles. January 1956. 
44p. diagrs., photos. (NACA TN 3590) 



INVESTIGATION OF FAR NOISE FIELD OF JETS. 
II - COMPARISON OF AIR JETS AND JET ENGINES. 
Willard D. Coles and Edmund E. Callaghan. 
January 1956. 19p. diagrs., photos. 
(NACA TN 3591) 



(1.1.4) 
AERODYNAMICS WITH HEAT 



DRAG MEASUREMENTS ON A 1/6-SCALE, FIN- 
LESS, STING-MOUNTED NACA RM-10 MISSILE IN 
FLIGHT AT MACH NUMBERS FROM 1.1 TO 4.04 
SHOWING SOME REYNOLDS NUMBER AND HEAT- 
ING EFFECTS. Robert O. Piland. October 1954. 
20p. diagrs., photos. (NACA RM L54H09) 



AN INVESTIGATION OF THE EFFECTS OF HEAT 
TRANSFER ON BOUNDARY- LAYER TRANSITION ON 
A PARABOLIC BODY OF REVOLUTION (NACA RM- 
10) AT A MACH NUMBER OF 1.61. K. R. Czarneckl 
and Archibald R. Sinclair. 1955. lip. diagrs., 
photos., tab. (NACA Rept. 1240. Supersedes 
TN 3165 and TN 3166) 



14 



(1) AERODYNAMICS 



VARIATION OF BOUNDARY -LAYER TRANSITION 
WITH HEAT TRANSFER ON TWO BODIES OF 
REVOLUTION AT A MACH NUMBER OF 3.12. 
John R. Jack and N. S. Diaconis. September 1955. 
16p. diagrs., photos. (NACA TN 3562) 



EFFECT OF TRANSVERSE BODY FORCE ON CHAN- 
NEL FLOW WITH SMALL HEAT ADDITION. Simon 
Ostrach and Franklin K. Moore. February 1956. 
31p. diagrs. (NACA TN 3594) 



SOME EFFECTS OF BLUNTNESS ON BOUNDARY- 
LAYER TRANSITION AND HEAT TRANSFER AT 
SUPERSONIC SPEEDS. W. E. Moeckel. March 
1956. 43p. diagrs. (NACA TN 3653) 



STABILITY OF SYSTEMS CONTAINING A HEAT 
SOURCE - THE RAYLEIGH CRITERION. Boa-Teh 

Chu, Johns Hopkins University. June 1956. 25p. 
diagrs. (NACA RM 56D27) 



(1. 1.4. 1) 
HEATING 



PRELIMINARY RESULTS OF SUPERSONIC-JET 
TESTS OF SIMPLIFIED WING STRUCTURES. 
Richard R. Heldenfeis and Richard Rosecrans. 
July 1953. I9p. diagrs., photos. 
(NACA RM L53E26a) 



TEST OF AN AERODYNAMICALLY HEATED 
MULTIWEB WING STRUCTURE (MW-1) IN A FREE 
JET AT MACH NUMBER 2. Richard R. Heldenfeis, 
Richard Rosecrans, and George E. Griffith. July 
1953. 37p. diagrs., photos. (NACA RM L53E27) 



TRANSIENT TEMPERATURE DISTRIBUTION IN AN 
AERODYNAMICALLY HEATED MULTIWEB WING. 
George E. Griffith. July 1953. 10p. diagrs. 
(NACA RM L53E27a) 



A STUDY OF BOUNDARY-LAYER TRANSITION AND 
SURFACE TEMPERATURE DISTRIBUTIONS AT 
MACH 3.12. Paul F. Brinich. July 1955. 39p. 
diagrs., photo. (NACA TN 3509) 



HEAT TRANSFER AT THE FORWARD STAGNATION 
POINT OF BLUNT BODIES. Eli Reshotko and 
Clarence B. Cohen. July 1955. 17p. diagrs. 
(NACA TN 3513) 



SOME EFFECTS OF JOINT CONDUCTIVITY ON THE 
TEMPERATURES AND THERMAL STRESSES IN 
AERODYNAMICALLY HEATED SKIN-STIFFENER 
COMBINATIONS. George E. Griffith and 
Georgene H. Miltonberger. June 1956. 62p- diagrs. 
(NACA TN 3699) 



(1. 1.4.2) 
HEAT TRANSFER 



WIRE CLOTH AS POROUS MATERIAL FOR 
TRANSPIRATION-COOLED WALLS. E. R. G. 
Eckert, Martin R. Kinsler, and Reeves P. Cochran. 
November 1951. 38p. diagrs., photos., tab. (NACA 
RM E51H23) 



PROCEDURE FOR CALCULATING TURBINE 
BLADE TEMPERATURES AND COMPARISON OF 
CALCULATED WITH OBSERVED VALUES FOR 
TWO STATIONARY AIR-COOLED BLADES. W. 
Byron Brown, Henry O. Slone, and Hadley T. 
Richards. September 1952. 38p. diagrs. (NACA 
RM E52H07) 



EFFECT OF VARIABLE VISCOSITY AND THERMAL 
CONDUCTIVITY ON HIGH-SPEED SLIP FLOW BE- 
TWEEN CONCENTRIC CYLINDERS. T. C. Lin and 
R. E. Street, University of Washington. 1954. ii, 
36p. diagrs. (NACA Rept. 1175. Formerly 
TN 2895) 



EXPERIMENTAL CONVECTIVE HEAT TRANSFER 
TO A 4-INCH AND 6-INCH HEMISPHERE AT MACH 
NUMBERS FROM 1.62 TO 3.04. Leo T. Chauvin 
and Joseph P. Maloney. February 1954. 18p. 
diagrs., photos. (NACA RM L53L08a) 



DRAG AND HEAT TRANSFER ON A PARABOLIC 
BODY OF REVOLUTION (NACA RM-10) IN FREE 
FLIGHT TO MACH NUMBER 2 WITH BOTH CON- 
STANT AND VARYING REYNOLDS NUMBER AND 
HEATING EFFECTS ON TURBULENT SKIN FRIC- 
TION. Joseph P. Maloney. June 1954. 34p. 
diagrs., photo. (NACA RM L54D06) 



CALCULATIONS OF LAMINAR HEAT TRANSFER 
AROUND CYLINDERS OF ARBITRARY CROSS 
SECTION AND TRANSPIRATION-COOLED WALLS 
WITH APPLICATION TO TURBINE BLADE 
COOLING. E. R. G. Eckert and J. N. B. 
Livingood. 1955. ii, 21p. diagrs., tabs. 
(NACA Rept. 1220. Supersedes RM E51F22) 



EXACT SOLUTIONS OF LAMINAR-BOUNDARY- 
LAYER EQUATIONS WITH CONSTANT PROPERTY 
VALUES FOR POROUS WALL WITH VARIABLE 
TEMPERATURE. Patrick L. Donoughe and John 
N. B. Livingood. 1955. ii, 21p. diagrs., tabs. 
(NACA Rept. 1229. Supersedes TN 3151) 



TURBULENT -HEAT -TRANSFER MEASUREMENTS 
AT A MACH NUMBER OF 1.62. Maurice J. 
Brevoort and Bernard Rashis. June 1955. 15p. 
diagrs., tab. (NACA TN 3461) 



RECOVERY AND TIME-RESPONSE CHARACTER- 
ISTICS pr SDC THERMOCOUPLE PROBES IN SUB- 
SONIC AND SUPERSONIC FLOW. Truman M. 
Stickney. July 1955. 25p. diagrs., photos., 2 tabs. 
(NACA TN 3455) 



15 



(1) AERODYNAMICS 



UNSTABLE CONVECTION IN VERTICAL CHANNELS 
WITH HEATING FROM BELOW, INCLUDING EF- 
FECTS OF HEAT SOURCES AND FRICTIONAL 
HEATING, Simon Ostrach. July 1955. 38p. diagrs., 
3 tabs. (NACA TN 3458) 



LAMINAR FREE CONVECTION ON A VERTICAL 
PLATE WITH PRESCRIBED NbNUNIFORM WALL 
HEAT FLUX OR PRESCRIBED NONUNIFORM WALL 
TEMPERATURE. E. M. Sparrow. July 1955. 34p. 
diagrs. (NACA TN 3508) 



HEAT TRANSFER AT THE FORWARD STAGNATION 
POINT OF BLUNT BODIES. Eli Reshotko and 
Clarence B. Cohen. July 1955. 17p. diagrs. 
(NACA TN 3513) 



VARIATION OF BOUNDARY-LAYER TRANSITION 
WITH HEAT TRANSFER ON TWO BODIES OF 
REVOLUTION AT A MACH NUMBER OF 3.12. 
John R. Jack and N. S. Diaconis. September 1955. 
16p. diagrs., photos. (NACA TN 3562) 



HEAT LOSS FROM YAWED HOT WIRES AT SUB- 
SONIC MACH NUMBERS. Virgil A. Sandborn and 
James C- Laurence. September 1955. 44p. 
diagrs., photo. (NACA TN 3563) 



AN EXPERIMENTAL COMPARISON OF THE 
LAGRANGIAN AND EULERIAN CORRELATION 
COEFFICIENTS IN HOMOGENEOUS ISOTROPIC 
TURBULENCE. William R. Mickelsen. October 
1955. 42p. diagrs. (NACA TN 3570) 



LAMINAR SEPARATION OVER A TRANSPIRATION- 
COOLED SURFACE IN COMPRESSIBLE FLOW. 
Morris Morduchow, Polytechnic Institute of Brook- 
lyn. December 1955. 32p. diagrs. 
(NACA TN 3559) 



SUMMARY OF LAMINAR-BOUNDARY-LAYER 
SOLUTIONS FOR WEDGE -TYPE FLOW OVER 
CONVECTION- AND TRANSPIRATION-COOLED 
SURFACES. John N. B. Livingood and Patrick L. 
Donoughe. December 1955. 33p. diagrs., tabs. 
(NACA TN 3588) 



TURBULENT HEAT-TRANSFER MEASUREMENTS 
AT A MACH NUMBER OF 0.87. Maurice J. 
Brevoort and Bernard Rashis. December 1955. 
13p. diagrs. {NACA TN 3599) 



EXPERIMENTAL INVESTIGATION OF AIR-FLOW 
UNIFORMITY AND PRESSURE LEVEL ON WIRE 
CLOTH FOR TRANSPIRATION-COOLING APPLI- 
CATIONS. Patrick L. Donoughe and Roy A. 
McKinnon, January 1956., 28p. diagrs., photos., 
tab. (NACA TN 3652. Supersedes RM E52E16) 



CORRELATION OF SUPERSONIC CONNECTIVE 
HEAT -TRANSFER COEFFICIENTS FROM MEAS- 
UREMENTS OF THE SKIN TEMPERATURE OF A 
PARABOLIC BODY OF REVOLUTION (NACA RM-10)i 
Leo T. Chauvin and Carlos A. deMoraes. March 
1956. 38p. diagrs., photo., tabs. (NACA TN 3623. 
Supersedes RM L51A18) 



(1.1.4.3) 
ADDITIONS OF HEAT 



ANALYSIS AND EXPERIMENTAL OBSERVATION OF 
PRESSURE LOSSES IN RAM-JET COMBUSTION 
CHAMBERS. William H. Sterbentz. November 4, 
1949. 22p. diagrs. (NACA RM E9H19) 



PRESSURE WAVES GENERATED BY ADDITION OF 
HEAT IN A GASEOUS MEDIUM. Boa-Teh Chu, 
Johng Hopkins University. June 1955. 47p. diagrs. 
(NACA TN 3411) 



(1.1.5) 
FLOW OF RAREFIED GASES 



A LOW-DENSITY WIND-TUNNEL STUDY OF 
SHOCK-WAVE STRUCTURE AND RELAXATION 
PHENOMENA IN GASES. F. S. Sherman, University 
of California. July 1955. 83p. diagrs., photos., 
2 tabs. (NACA TN 3298) 



(1.1.5. 1) 
SLIP FLOW 



EFFECT OF VARIABLE VISCOSITY AND THERMAL 
CONDUCTIVITY ON HIGH-SPEED SLIP FLOW BE- 
TWEEN CONCENTRIC CYLINDERS. T. C. Lin and 
R. E. Street, University of Washington. 1954. ii, 
36p. diagrs. (NACA Rept. 1175. Formerly 
TN 2895) 



16 



(1) AERODYNAMICS 



(1.2) 
Wing* 



THE BASE PRESSURE AT SUPERSONIC SPEEDS 
ON TWO-DIMENSIONAL AIRFOILS AND BODIES OF 
REVOLUTION (WITH AND WITHOUT FINS) HAVING 
TURBULENT BOUNDARY LAYERS. Eugene S. Love. 
April 1953. 65p. diagrs., photos. ' (NACA 
RM L53C02) 



A UNIFIED TWO-DIMENSIONAL APPROACH TO 
THE CALCULATION OF THREE-DIMENSIONAL 
HYPERSONIC FLOWS, WITH APPLICATION TO 
BODIES OF REVOLUTION. A. J. Eggers, Jr. and 
Raymond C. Savin. 1955. ii, 27p. diagrs., tab. 
(NACA Rept. 1249. Supersedes TN 2811) 



REMARK ON THE THEORY OF LIFTING SUR- 
FACES. (Sulla teoria delle superficl portantl). 
Aldo Muggia. January 1956. lip. diagrs. 
(NACA TM 1386. Trans, from Atti della Accademia 
deUe Scienze di Torino, v. 87, 1952-1953) 



(1.2.1) 
WING SECTIONS 



EFFECTS OF BASE BLEED ON THE BASE PRES- 
SURE OF BLUNT -TRAILING-EDGE AIRFOILS AT 
SUPERSONIC SPEEDS. William R. Wimbrow. 
March 1954. 33p. diagrs., photos. 
(NACA RM A54A07) 



(1.2.1. 1) 
SECTION THEORY 



THEORETICAL PREDICTION OF PRESSURE DIS- 
TRIBUTIONS ON NONLIFTING AIRFOILS AT HIGH 
SUBSONIC SPEEDS. John R. Spreiter and Alberta 
Alksne. 1955. iii, 42p. diagrs., photos. 
(NACA Rept. 1217. Supersedes TN 3096) 



CALCULATION OF THE SUPERSONIC PRESSURE 
DISTRIBUTION ON A SINGLE-CURVED TAPERED 
WING IN REGIONS NOT INFLUENCED BY THE ROOT 
OR TIP. Walter G. Vincenti and Newman H. Fisher, 
Jr. June 1955. 32p. diagrs. (NACA TN 3499) 



(1. 2. 1. 2) 
SECTION VARIABLES 



THE EFFECT OF REYNOLDS NUMBER ON THE 
STALLING CHARACTERISTICS AND PRESSURE 
DISTRIBUTIONS OF FOUR MODERATELY THIN 

AIRFOIL SECTIONS. George B. McCullough. 
November 1955. 24p. diagrs., tabs. 
(NACA TN 3524) 



(1.2. 1.2. 1) 
Camber 

INVESTIGATION OF THE LOW^SFEED AERO- 
DYNAMIC CHARACTERISTICS OF A VARIABLE - 
SWEEP AIRPLANE MODEL WITH A WING HAVING 
PARTIAL-SPAN CAMBERED- LEADING-EDGE 
MODIFICATIONS. Robert E. Becht and Andrew L. 
Byrnes, Jr. September 1952. 47p. diagrs., photos. 
(NACA RM L52G08a) 



A FLIGHT INVESTIGATION OF THE EFFECT OF 
LEADING-EDGE CAMBER ON THE AERODYNAMIC 
CHARACTERISTICS OF A SWEPT -WING AIRPLANE. 
Seth B. Anderson, Frederick H. Matteson, and 
Rudolph D. Van Dyke, Jr. February 1953. 23p. 
diagrs., photos., tab. (NACA RM A52L16a) 



DETERMINATION OF MEAN CAMBER SURFACES 
FOR WINGS HAVING UNIFORM CHORDWISE LOAD- 
ING AND ARBITRARY SPANWISE LOADING IN 
SUBSONIC FLOW. S. Katzoff, M. Frances Faison 
and Hugh C. DuBose. 1954. ii, 17p. diagrs., tab. 
(NACA Rept. 1176. Formerly TN 2908) 



EFFECTS OF HIGH-LIFT DEVICES AND 
HORIZONTAL-TAIL LOCATION ON THE LOW- 
SPEED CHARACTERISTICS OF A LARGE-SCALE 
45° SWEPT-WING AIRPLANE CONFIGURATION. 
Ralph L. Maki and Ursel R. Embry. August 1954. 
46p. diagrs., photo., tabs. (NACA RM A54E10) 



EFFECT OF THICKNESS, CAMBER, AND THICK- 
NESS DISTRIBUTION ON AIRFOIL CHARACTERIS- 
TICS AT MACH NUMBERS UP TO 1.0. Bernard N. 
Daley and Richard S. Dick. March 1956. 75p. 
diagrs., photos., tab. (NACA TN 3607. Supersedes 
RM L52G31a) 



(1.2. 1.2.2) 
Thickness 

FREE-FLIGHT INVESTIGATION OF CONTROL EF- 
FECTIVENESS OF FULL-SPAN, 0.2-CHORD PLAIN 
AILERONS AT HIGH SUBSONIC, TRANSONIC, AND 
SUPERSONIC SPEEDS TO DETERMINE SOME EF- 
FECTS OF WING SWEEPBACK TAPER, ASPECT 
RATIO, AND SECTION-THICKNESS RATIO. Carl A. 
Sandahl. August 13, 1947. 16p. diagrs., photos., 
tab. (NACA RM L7F30) 



LONGITUDINAL FLIGHT CHARACTERISTICS OF 
THE BELL X-5 RESEARCH AIRPLANE AT 59° 
SWEEPBACK WITH MODIFIED WING ROOTS. 
James A. Martin. August 1953. 25p. diagrs., 
photos., tab. (NACA RM L53E28) 



17 



(1) AERODYNAMICS 



FLIGHT MEASUREMENTS OF LIFT AND DRAG 
FOR THE BELL X-l RESEARCH AIRPLANE HAV- 
ING A 10-PERCENT-THICK WING. Edwin J. 
Saltzman. September 1953. 37p. diagrs., tab. 
(NACA RM L53F08) 



SUPERSONIC FLOW PAST OSCILLATING AIRFOILS 
INCLUDING NONLINEAR THICKNESS EFFECTS. 
Milton D. Van Dyke. 1954. ii, 17p. diagrs. (NACA 
Rept. 1183. Formerly TN 2982) 



THEORETICAL PREDICTION OF PRESSURE DIS- 
TRIBUTIONS ON NONLIFTING AIRFOILS AT HIGH 
SUBSONIC SPEEDS. John R, Spreiter and Alberta 
Alksne. 1955. in, 42p. diagrs., photos. 
(NACA Rept. 1217. Supersedes TN 3096) 



EFFECT OF THICKNESS, CAMBER, AND THICK- 
NESS DISTRIBUTION ON AIRFOIL CHARACTERIS- 
TICS AT MACH NUMBERS UP TO 1.0. Bernard N. 
Daley and Richard S. Dick. March 1956. 75p. 
diagrs., photos., tab. (NACA TN 3607. Supersedes 
RM L52G31a) 



EXPERIMENTAL INVESTIGATION OF THE FLOW 
AROUND LIFTING SYMMETRICAL DOUBLE- 
WEDGE AIRFOILS AT MACH NUMBERS OF 1.30 
AND 1.41. Paul B. Gooderum and George P. Wood. 
March 1956. 86p. diagrs., photos. 
(NACA TN 3626) 



RESULTS OF A FLIGHT INVESTIGATION TO DE- 
TERMINE THE ZERO-LIFT DRAG CHARACTER- 
ISTICS OF A 60° DELTA WING WITH NACA 65-006 
AIRFOIL SECTION AND VARIOUS DOUBLE-WEDGE 
SECTIONS AT MACH NUMBERS FROM 0.7 TO 1.6. 
Clement J. Welsh. April 1956. 13p. diagrs., 
photo. (NACA TN 3650. Supersedes RM L50F01) 



(1.2. 1. 2.3) 
Thickness Distribution 



EFFECTS OF SOME AIRFOIL -SECTION VARIA- 
TIONS ON WING-AILERON ROLLING EFFECTIVE- 
NESS AND DRAG AS DETERMINED IN FREE 
FLIGHT AT TRANSONIC AND SUPERSONIC SPEEDS. 
Carl A. Sandahl, William M. Bland, Jr., and H. Kurt 
Strass. July 22, 1949. 29p. diagrs., photos., tabs. 
(NACA RM L9D12) 



AN EXPERIMENTAL INVESTIGATION OF THE 
ZERO-LIFT -DRAG CHARACTERISTICS OF SYM- 
METRICAL BLUNT-TRAILING-EDGE AIRFOILS AT 
MACH NUMBERS FROM 2.7 TO 5.0. Clarence A. 
Syvertson and Hermilo R. Gloria. April 1953. 31p. 
diagrs., photos., tabs. (NACA RM A53B02) 



MEASUREMENTS OF NORMAL-FORCE- 
COEFFICIENT FLUCTUATION ON FOUR 9- 
PERCENT-THICK AIRFOILS HAVING DIFFERENT 
LOCATIONS OF MAXIMUM THICKNESS. Milton D. 
Humphreys. April 1954. 21p, diagrs., photos. 
(NACA RM L54B22) 



EFFECT OF TRAILING-EDGE THICKNESS ON LIFT 
AT SUPERSONIC VELOCITIES. Dean R. Chapman 
and Robert H. Kester. June 1955. 19p. diagrs. 
(NACA TN 3504. Formerly RM A52D17) 



EFFECT OF THICKNESS, CAMBER, AND THICK- 
NESS DISTRIBUTION ON AIRFOIL CHARACTERIS- 
TICS AT MACH NUMBERS UP TO 1.0. Bernard N. 
Daley and Richard S. Dick. March 1956. 75p. 
•diagrs., photos., tab. (NACA TN 3607. Supersedes 
RM L52G31a) 



RESULTS OF A FLIGHT INVESTIGATION TO DE- 
TERMINE THE ZERO-LIFT DRAG CHARACTER- 
ISTICS OF A 60° DELTA WING WITH NACA 65-006 
AIRFOIL SECTION AND VARIOUS DOUBLE-WEDGE 
SECTIONS AT MACH NUMBERS FROM 0.7 TO 1.6. 
Clement J. Welsh. April 1956. 13p. diagrs., 
photo. (NACA TN 3650. Supersedes RM L50F01) 



(1.2. 1.2.5) 

Surface Conditions 

IMPINGEMENT OF CLOUD DROPLETS ON A CYL- 
INDER AND PROCEDURE FOR MEASURING LIQUID- 
WATER CONTENT AND DROPLET SIZES IN SUPER- 
COOLED CLOUDS BY ROTATING MULTICYLINDER 
METHOD. R. J. Brun, W. Lewis, P. J. Perkins 
and J. S. Serafini. Appendix E: ALTERNATE 
METHOD OF REDUCING ROTATING MULTICYL- 
INDER DATA. PaulT. Hacker. 1955. iv, 43p. 
diagrs., photos., tabs. (NACA Rept. 1215. Super- 
sedes TN 2903; TN 2904; RM E53D23) 



IMPINGEMENT OF WATER DROPLETS ON NACA 
65A004 AIRFOIL AT 0° ANGLE OF ATTACK. 
Rinaldo J. Brun and Dorothea E. Vogt. November 
1955. 28p. diagrs. (NACA TN 3586) 



EFFECT OF PNEUMATIC DE-ICERS AND ICE 
FORMATIONS ON AERODYNAMIC CHARACTERIS- 
TICS OF AN AIRFOIL. Dean T. Bowden. February 
1956. 59p. diagrs., photos. (NACA TN 3564) 



(1.2.1. 3) 
DESIGNATED PROFILES 



FREE-FLIGHT INVESTIGATION OF CONTROL EF- 
FECTIVENESS OF FULL-SPAN, 0.2-CHORD PLAIN 
AILERONS AT HIGH SUBSONIC, TRANSONIC, AND 
SUPERSONIC SPEEDS TO DETERMINE SOME EF- 
FECTS OF WING SWEEPBACK, TAPER, ASPECT 
RATIO, AND SECTION-THICKNESS RATIO. Carl A. 
Sandahl. August 13, 1947. 16p. diagrs., photos., 
tab. (NACA RM L7F30) 



AERODYNAMIC CHARACTERISTICS OF FOUR 
WINGS OF SWEEPBACK ANGLES 0°, 35°, 45°, AND 
60°, NACA 65A006 AIRFOIL SECTION, ASPECT 
RATIO 4, AND TAPER RATIO 0.6 IN COMBINATION 
WITH A FUSELAGE AT HIGH SUBSONIC MACH 
NUMBERS AND AT A MACH NUMBER OF 1.2. 
Arvo A. Luoma. June 6, 1951. 59p. diagrs., photo., 
tab. (NACA RM L51D13) 



18 



(1) AERODYNAMICS 



REDUCTION OF PROFILE DRAG AT SUPERSONIC 
VELOCITIES BY THE USE OF AIRFOIL SECTIONS 
HAVING A BLUNT TRAILING EDGE. Dean R. 
Chapman. September 1955. 29p. diagrs. , photo. 
(NACA TN 3503. Supersedes RM A9H11) 



AN EXPERIMENTAL INVESTIGATION OF REGIONS 
OF SEPARATED LAMINAR FLOW. Donald E. 
Gault. September 1955. 65p. diagrs., photos., 4 tabs. 
(NACA TN 3505) 



FLIGHT INVESTIGATION AT MACH NUMBERS 
FROM 0.6 TO 1.7 TO DETERMINE DRAG AND 
BASE PRESSURES ON A BLUNT-TRAJLING-EDGE 
AIRFOIL AND DRAG OF DIAMOND AND CIRCULAR- 
ARC AIRFOILS AT ZERO LIFT. John D. Morrow 
and Ellis Katz. November 1955. 19p. diagrs., 
photos. (NACA TN 3548. Supersedes RM L50E19a) 



MEASUREMENTS OF THE EFFECT OF TRAILING- 
EDGE THICKNESS ON THE ZERO-LIFT DRAG OF 
THIN LOW-ASPECT-RATIO WINGS. John D. 
Morrow. November 1955. lip. diagrs., photo. 
(NACA TN 3550. Supersedes RM L50F26) 



EXPERIMENTAL INVESTIGATION OF THE FLOW 
AROUND LIFTING SYMMETRICAL DOUBLE- 
WEDGE AIRFOILS AT MACH NUMBERS OF 1.30 
AND 1.41. Paul B. Gooderum and George P. Wood. 
March 1956. 86p. diagrs., photos. 
(NACA TN 3626) 



(1.2.1.5) 

CONTROLS 



(1.2. 1.5.1) 
Flap Type 



EFFECTS OF SWEEP ON CONTROLS. John G. 
Lowry John A. Axelson, and Harold I. Johnson. 
June 3, 1948. 29p. diagrs. (NACA RM L8A28c) 



PRELIMINARY DATA AT A MACH NUMBER OF 2.40 
OF THE CHARACTERISTICS OF FLAP-TYPE CON- 
TROLS EQUIPPED WITH PLAIN OVERHANG BAL- 
ANCES. James N. Mueller and K. R. Czarnecki. 
September 1952. 43p. diagrs., photos. 
(NACA RML52F10) 



AILERON AND ELEVATOR HINGE MOMENTS OF 
THE BELL X-l AIRPLANE MEASURED IN TRAN- 
SONIC FLIGHT. Hubert M. Drake and John B. 
McKay. June 1953. 27p. diagrs. 
(NACA RM L53E04) 



(1.2.1.5.2) 
Spoilers 

EXPERIMENTAL INVESTIGATION OF THE OSCIL- 
LATING FORCES AND MOMENTS ON A TWO- 
DIMENSIONAL WING EQUIPPED WITH AN OSCIL- 
LATING CIRCULAR-ARC SPOILER. Sherman A. 
Clevenson and John E. Tomassoni. January 1954. 
20p. diagrs., photos. (NACA RM L53K18) 



(1. 2. 1. 6) 
BOUNDARY LAYER 



AN INVESTIGATION OF FOUR WINGS OF SQUARE 
PLAN FORM AT A MACH NUMBER OF 6.86 IN THE 
LANGLEY 11-INCH HYPERSONIC TUNNEL. 
Charles H. McLelLan, Mitchel H. Bertram, and 
John A. Moore. June 1951. 47p. diagrs., photos. 
(NACA RM L51D17) 



THE EFFECT OF REYNOLDS NUMBER ON THE 
STALLING CHARACTERISTICS AND PRESSURE 
DISTRIBUTIONS OF FOUR MODERATELY THIN 
AIRFOIL SECTIONS. George B. McCullough. 
November 1955. 24p. diagrs., tabs. 
(NACA TN 3524) 



LIFT HYSTERESIS AT STALL AS AN UNSTEADY 
BOUNDARY-LAYER PHENOMENON. Franklin K. 
Moore. November 1955. 32p. diagrs., tab. 
(NACA TN 3571) 



PRELIMINARY FLIGHT SURVEY OF AERODY- 
NAMIC NOISE ON AN AIRPLANE WING. Harold R. 
Mull and Joseph S. Algranti. March 1956. 8p. 
diagrs. (NACA RM E55K07) 



PRELIMINARY REPORT ON A STUDY OF SEPA- 
RATED FLOWS IN SUPERSONIC AND SUBSONIC 
STREAMS. Dean R. Chapman, Donald M. Kuehn, 
and Howard K. Larson. June 1956. 15p. diagrs., 
photos. (NACA RM A55L14) 



(1. 2.1.6. 1) 
Characteristics 



EFFECTS OF SWEEP AND ANGLE OF ATTACK ON 
BOUNDARY-LAYER TRANSITION ON WINGS AT 
MACH NUMBER 4.04. Robert W. Dunning and 
Edward F. Ulmann. August 1955. 31p. diagrs., 
photos. (NACA TN 3473) 



AN EXPERIMENTAL INVESTIGATION OF REGIONS 
OF SEPARATED LAMINAR FLOW. Donald E. 
Gault. September 1955. 65p. diagrs., photos., 4 tabs. 
(NACA TN 3505) 



19 



( 1 ) AERODYNAMICS 



(1.2. 1.6.2) 
Control 



PRESSURE RISE ASSOCIATED WITH SHOCK- 
INDUCED BOUNDARY -LAYER SEPARATION. 
Eugene S. Love. December 1955. 32p. diagrs. 
(NACA TN 3601) 



ON THE PERMEABILITY OF POROUS MATERIALS. 
E. Carson Yates, Jr. January 1956. 31p. diagrs. 
(NACA TN 3596) 



PERFORATED SHEETS AS A POROUS MATERIAL 
FOR DISTRIBUTED SUCTION AND INJECTION. 
Robert E. Dannenberg, Bruno J. Gambucci, and 
James A. Weiberg. April 1956. 27p. diagrs., 
photos. (NACA TN 3669) 



(1. 2. 1.7) 
REYNOLDS NUMBER EFFECTS 



AN EXPERIMENTAL INVESTIGATION OF THE 
ZERO-LIFT-DRAG CHARACTERISTICS OF SYM- 
METRICAL BLUNT-TRAILING-EDGE AIRFOILS AT 
MACH NUMBERS FROM 2.7 TO 5.0. Clarence A. 
Syvertson and Hermilo R. Gloria. April 1953. 31p. 
diagrs., photos., tabs. (NACA RM A53B02) 



EFFECTS OF BASE BLEED ON THE BASE PRES- 
SURE OF BLUNT-TRAILING-EDGE AIRFOILS AT 
SUPERSONIC SPEEDS. William R. Wimbrow. 
March 1954. 33p. diagrs., photos. 
(NACA RM A54A07) 



EFFECTS OF SWEEP AND ANGLE OF ATTACK ON 
BOUNDARY-LAYER TRANSITION ON WINGS AT 
MACH NUMBER 4.04. Robert W. Dunning and 
Edward F. Ulmann. August 1955. 31p. diagrs., 
photos. (NACA TN 3473) 



AN EXPERIMENTAL INVESTIGATION OF REGIONS 
OF SEPARATED LAMINAR FLOW. Donald E. 
Gault. September 1955. 65p. diagrs., photos., 4 tabs. 
(NACA TN 3505) 



(1. 2. 1. 8) 
MACH NUMBER EFFECTS 



MEASUREMENTS OF THE CHORDWISE PRESSURE 
DISTRIBUTIONS OVER THE WING OF THE XS-1 
RESEARCH AIRPLANE IN FLIGHT. De E. Beeler, 
Milton D. McLaughlin, and Dorothy C. Clift. 
August 4, 1948. 35p. diagrs., photo., tab. (NACA 
RM L8G21) 



REVIEW OF SOME RECENT DATA ON BUFFET 
BOUNDARIES. Paul E. Purser and John A. Wyss. 
May 23, 1951. lip. diagrs. (NACA RM L51E02a) 



A CORRELATION WITH FLIGHT TESTS OF RE- 
SULTS OBTAINED FROM THE MEASUREMENT OF 
WING PRESSURE DISTRIBUTIONS ON A 1/4-SCALE 
MODEL OF THE X-l AIRPLANE (10-PERCENT - 
THICK WING). Jack F. Runckel and James H. 
Henderson. September 1952. 60p. diagrs., photos., 
tab. (NACA RM L52E29) 



AN EXPERIMENTAL INVESTIGATION OF THE 
ZERO-LIFT-DRAG CHARACTERISTICS OF SYM- 
METRICAL BLUNT-TRAILING-EDGE AIRFOILS AT 
MACH NUMBERS FROM 2.7 TO 5.0. Clarence A. 
Syvertson and Hermilo R. Gloria. April 1953. 31p. 
diagrs., photos., tabs. (NACA RM A53B02) 



AILERON AND ELEVATOR HINGE MOMENTS OF 
THE BELL X-l AIRPLANE MEASURED IN TRAN- 
SONIC FLIGHT. Hubert M. Drake and John B. 
McKay. June 1953. 27p. diagrs. 
(NACA RM L53E04) 



EFFECTS OF BASE BLEED ON THE BASE PRES- 
SURE OF BLUNT-TRAILING-EDGE AIRFOILS AT 
SUPERSONIC SPEEDS. William R. Wimbrow. 
March 1954. 33p. diagrs., photos. 
(NACA RM A54A07) 



MEASUREMENTS OF NORMAL-FORCE- 
COEFFICIENT FLUCTUATION ON FOUR 9- 
PERCENT-THICK AIRFOILS HAVING DIFFERENT 
LOCATIONS OF MAXIMUM THICKNESS. Milton D. 
Humphreys. April 1954. 21p. diagrs., photos. 
(NACA RM L54B22) 



THEORETICAL PREDICTION OF PRESSURE DIS- 
TRIBUTIONS ON NONLIFTING AIRFOILS AT HIGH 
SUBSONIC SPEEDS. John R. Spreiter and Alberta 
Alksne. 1955. iii, 42p. diagrs., photos. 
(NACA Rept. 1217. Supersedes TN 3096) 



EFFECTS OF SWEEP AND ANGLE OF ATTACK ON 
BOUNDARY-LAYER TRANSITION ON WINGS AT 
MACH NUMBER 4.04. Robert W. Dunning and 
Edward F. Ulmann. August 1955. 31p. diagrs., 
photos. (NACA TN 3473) 



EFFECT OF THICKNESS, CAMBER, AND THICK- 
NESS DISTRIBUTION ON AIRFOIL CHARACTERIS- 
TICS AT MACH NUMBERS UP TO 1.0. Bernard N. 
Daley and Richard S. Dick. March 1956. 75p. 
diagrs., photos., tab. (NACA TN 3607. Supersedes 
RM L52G31a) 



EXPERIMENTAL INVESTIGATION OF THE FLOW 
AROUND LIFTING SYMMETRICAL DOUBLE- 
WEDGE AIRFOILS AT MACH NUMBERS OF 1.30 
AND 1.41. Paul B. Goo de rum and George P. Wood. 
March 1956. 86p. diagrs., photos. 
(NACA TN 3626) 



20 



(1 ) AERODYNAMICS 



(1.2.1.9) 
WAKE 

EFFECTS OF BASE BLEED ON THE BASE PRES- 
SURE OF BLUNT -TRAILING-EDGE AIRFOILS AT 
SUPERSONIC SPEEDS. William R. Wimbrow. 
March 1954. 33p. diagrs., photos. 
(NACA RM A54A07) 



THEORETICAL LOSS RELATIONS FOR LOW- 
SPEED TWO-DIMENSIONAL -CASCADE FLOW. 
Seymour Lieblein and William H. Roudebush. 
March 1956. 46p. diagrs., tab. (NACA TN 3662) 



(1.2.2) 
COMPLETE WINGS 

THE TRANSONIC CHARACTERISTICS OF A LOW- 
ASPECT-RATIO TRIANGULAR WING WITH A 
CONSTANT-CHORD FLAP AS DETERMINED BY 
WING-FLOW TESTS, INCLUDING CORRELATION 
WITH LARGE-SCALE TESTS. George A. Rathert, 
Jr., L. Stewart Rolls, and Carl M. Hanson. 
July 18, 1950. 39p. diagrs., photo. 
(NACA RM A50E10) 



AN INVESTIGATION OF FOUR WINGS OF SQUARE 
PLAN FORM AT A MACH NUMBER OF 6.86 IN THE 
LANGLEY 11 -INCH HYPERSONIC TUNNEL. 
Charles H. McLellan, Mitchel H. Bertram, and 
John A. Moore. June 1951. 47p. diagrs., photos. 
(NACA RML51D17) 



PRELIMINARY INVESTIGATION AT SUBSONIC AND 
TRANSONIC SPEEDS OF THE AERODYNAMIC 
CHARACTERISTICS OF A BIPLANE COMPOSED OF 
A SWEPTBACK AND A SWEPTFORWARD WING 
JOINED AT THE TIPS. Jones F. Cahill and 
Dexter H. Stead. March 1954. 19p. diagrs., 
photos. (NACA RM L53L24b) 



A WIND-TUNNEL INVESTIGATION OF A 0.4-SCALE 
MODEL OF AN ASSAULT -TRANSPORT AIRPLANE 
WITH BOUNDARY-LAYER CONTROL APPLIED. 
Marvin P. Fink, Bennie W. Cocke, and Stanley 
Lipson. May 1956. 63p. diagrs., photos. 
(NACA RM L55G26a) 



(1. 2. 2. 1) 

WING THEORY 



EXPERIMENTAL DETERMINATION OF EFFECT 
OF STRUCTURAL RIGIDITY ON ROLLING EFFEC- 
TIVENESS OF SOME STRAIGHT AND SWEPT WINGS 
AT MACH NUMBERS FROM 0.7 TO 1.7. H. Kurt 
Strass, E. M. Fields, and Paul E. Purser. 
October 4, 1950. 40p. diagrs., photo., tab. (NACA 
RM L50G14b) * 



A COMPARISON OF THE EXPERIMENTAL AND 
THEORETICAL LOADING OVER TRIANGULAR 
WINGS IN SIDESLIP AT SUPERSONIC SPEEDS. 
John W. Boyd. May 18, 1951. 58p. diagrs., photo., 
tabs. (NACA RM A51C13) 



DOWNWASH AND SIDEWASH FIELDS BEHIND 
CRUCIFORM WINGS. John R. Spreiter. January 
1952. 18p, photos., diagrs. (NACA RM A51L17) 



COMPARISON OF MEASURED AND PREDICTED 
INDICATED ANGLES OF ATTACK NEAR THE 
FUSELAGES OF A TRIANGULAR-WING WIND- 
TUNNEL MODEL AND A SWEPT -WING FIGHTER 
AIRPLANE IN FLIGHT. Norman M. McFadden, 
John L. McCloud, HI, and Harry A. James. 
March 1953. 13p. diagrs. (NACA RM A53A15) 



DETERMINATION OF MEAN CAMBER SURFACES 
FOR WINGS HAVING UNIFORM CHORDWISE LOAD- 
ING AND ARBITRARY SPANWISE LOADING IN 
SUBSONIC FLOW. S. Katzoff, M. Frances Faison 
and Hugh C. DuBose. 1954. ii, 17p. diagrs., tab. 
(NACA Rept. 1176. Formerly TN 2908) 



A COMPARISON OF THE SPANWISE LOADING 
CALCULATED BY VARIOUS METHODS WITH EX- 
PERIMENTAL LOADINGS OBTAINED ON A 45° 
SWEPTBACK WING OF ASPECT RATIO 8.02 AT A 
REYNOLDS NUMBER OF 4.0 x 10 6 . William C. 
Schneider. 1954. ii, lip. diagrs., tab. 
(NACA Rept. 1208. Supersedes RM L51G30) 



COMPARISON BETWEEN THEORETICAL AND EX- 
PERIMENTAL RATES OF ROLL OF TWO MODELS 
WITH FLEXIBLE RECTANGULAR WINGS AT SU- 
PERSONIC SPEEDS. John M. Hedgepeth and 
Robert J. Kell. August 1954. 21p. diagrs., photo., 
tabs. (NACA RM L54F23) 



A METHOD FOR THE DESIGN OF SWEPTBACK 

WINGS WARPED TO PRODUCE SPECIFIED FLIGHT 
CHARACTERISTICS AT SUPERSONIC SPEEDS. 
Warren A. Tucker. 1955. i, 17p. diagrs., tabs. 
(NACA Rept. 1226. Supersedes RM L51F08) 



GENERALIZED INDICIAL FORCES ON DEFORMING 
RECTANGULAR WINGS IN SUPERSONIC FLIGHT. 
Harvard Lomax, Franklyn B. Fuller and Loma 
Sluder. 1955. ii, 27p. diagrs., tab. 
(NACA Rept. 1230. Supersedes TN 3286) 



A CORRELATION BY MEANS OF TRANSONIC 
SIMILARITY RULES OF EXPERIMENTALLY DE- 
TERMINED CHARACTERISTICS OF A SERIES OF 
SYMMETRICAL AND CAMBERED WINGS OF 
RECTANGULAR PLAN FORM. John B. McDevitt. 
1955. ii, 23p. diagrs., tabs. (NACA Rept. 1253. 
Supersedes RM A51L17b; RM A53G31) 



21 



(1 ) AERODYNAMICS 



CALCULATION OF THE SUPERSONIC PRESSURE 
DISTRIBUTION ON A SINGLE-CURVED TAPERED 
WING IN REGIONS NOT INFLUENCED BY THE ROOT 
OR TIP. Walter G. Vincenti and Newman H. Fisher, 
Jr. June 1955. 32p. diagrs. (NACA TN 3499) 



AERODYNAMICS OF A RECTANGULAR WING OF 
INFINITE ASPECT RATIO AT HIGH ANGLES OF 
ATTACK AND SUPERSONIC SPEEDS. John C. 
Martin and Frank S. Malvestuto, Jr. July 1955. 
114p. diagrs., tab. (NACA TN 3421) 



CORRECTION OF ADDITIONAL SPAN LOADINGS 
COMPUTED BY THE WEISSINGER SEVEN-POINT 
METHOD FOR MODERATELY TAPERED WINGS 
OF HIGH ASPECT RATIO. John DeYoung and 
Walter H. Barling, Jr. July 1955. 31p. diagrs. 
(NACA TN 3500) 



THE PROPER COMBINATION OF LIFT LOADING 
FOR LEAST DRAG ON A SUPERSONIC WING. 
Frederick C. Grant. October 1955. 21p. diagrs. 
(NACA TN 3533) 



A THEORETICAL STUDY OF THE AERODYNAMICS 
OF SLENDER CRUCIFORM-WING ARRANGEMENTS 
AND THEIR WAKES. John R. Spreiter and Alvln H. 
Sacks. March 1956. i, 67p. diagrs., photos., tabs. 
(NACA TN 3528) 



AN ANALYSIS OF ESTIMATED AND EXPERI- 
MENTAL TRANSONIC DOWNWASH CHARACTER- 
ISTICS AS AFFECTED BY PLAN FORM AND THICK- 
NESS FOR WING AND WING- FUSELAGE CONFIG- 
URATIONS. Joseph Weil, George S. Campbell and 
Margaret S. Diederich. April 1956. 92p. diagrs., 
photos., tabs. (NACA TN 3628. Supersedes 
RM L52I22) 



THEORETICAL PRESSURE DISTRIBUTIONS FOR 
SOME SLENDER WING-BODY COMBINATIONS AT 
ZERO LIFT. Paul F. Byrd. April 1956. 39p. 
diagrs. (NACA TN 3674. Supersedes RM A54J07) 



ON THE RANGE OF APPLICABILITY OF THE 
TRANSONIC AREA RULE. John R. Spreiter. 
May 1956. 21p. diagrs. (NACA TN 3673. Super- 
sedes RM A54F28) 



COMPARISON BETWEEN EXPERIMENTAL AND 
PREDICTED DOWNWASH AT A MACH NUMBER OF 
0.25 BEHIND A WING-BODY COMBINATION HAVING 
A TRIANGULAR WING OF ASPECT RATIO 2.0. 
Norman E. Sorensen and Edward J. Hopkins. May 
1956. 29p. diagrs., photos. (NACA TN 3720) 



FLIGHT TESTS AT SUPERSONIC SPEEDS TO 
DETERMINE THE EFFECT OF TAPER ON THE 
ZERO-LIFT DRAG OF SWEPTBACK LOW -ASPECT- 
RATIO WINGS. Murray Pittel. June 1956. 20p. 
diagrs., photos. (NACA TN 3697. Supersedes 
RM L50F30a) 



(1.2.2.2.) 
WING VARIABLES 



WING-DROPPING CHARACTERISTICS OF SOME 
STRAIGHT AND SWEPT WINGS AT TRANSONIC 
SPEEDS AS DETERMINED WITH ROCKET- 
POWERED MODELS. David G. Stone. May 26, 
1950. 12p. diagrs., tab. (NACA RM L50C01) 



TABULATED PRESSURE COEFFICIENTS AND 
AERODYNAMIC CHARACTERISTICS MEASURED ON 
THE WING OF THE BELL X-l AIRPLANE IN PULL- 
UPS AT MACH NUMBERS FROM 0.53 TO 0.99. 
Ronald J. Knapp and Gertrude V. Wllken. 
November 1, 1950. 77p. diagrs., photo., 11 tabs. 
(NACA RM L50H28) 



TABULATED PRESSURE COEFFICIENTS AND 
AERODYNAMIC CHARACTERISTICS MEASURED 
ON THE WING OF THE BELL X-l AIRPLANE IN 
AN UNACCELERATED STALL AND IN PULL-UPS 
AT MACH NUMBERS OF 0.74, 0.75, 0.94, AND 
0.97. Lawrence A. Smith. June 19, 1951. 49p. 
diagrs., photo., tabs. (NACA RM L51B23) 



INVESTIGATION OF THE EFFECTS OF TWIST AND 
CAMBER ON THE AERODYNAMIC CHARACTER- 
ISTICS OF A 50° 38' SWEPTBACK WING OF AS- 
PECT RATIO 2.98. TRANSONIC-BUMP METHOD. 
Kenneth P. Spreemann and William J. Alford, Jr. 
August 1951. 33p. diagrs., photos., tab. 
(NACA RML51C16) 



DAMPING IN ROLL OF STRAIGHT AND 45° SWEPT 
WINGS OF VARIOUS TAPER RATIOS DETERMINED 
AT HIGH SUBSONIC, TRANSONIC, AND SUPER- 
SONIC SPEEDS WITH ROCKET-POWERED 
MODELS. E. Claude Sanders, Jr. October ly51. 
15p. diagrs. (NACA RM L51H14) 



DAMPING IN ROLL OF MODELS WITH 45°, 60°, 
AND 70° DELTA WINGS DETERMINED AT HIGH 
SUBSONIC, TRANSONIC, AND SUPERSONIC 
SPEEDS WITH ROCKET-POWERED MODELS. 
E. Claude Sanders, Jr. June 1952. 18p. diagrs., 
photos. (NACA RM L52D22a) 



EFFECTS OF HORIZONTAL-TAIL HEIGHT AND A 
WING LEADING-EDGE MODIFICATION CON- 
SISTING OF A FULL-SPAN FLAP AND A PARTIAL- 
SPAN CHORD-EXTENSION ON THE AERODYNAMIC 
CHARACTERISTICS IN PITCH AT HIGH SUBSONIC 
SPEEDS OF A MODEL WITH A 45° SWEPTBACK 
WING. William D. Morrison, Jr. and William J. 
Alford, Jr. June 1953. 37p. diagrs., photo., tab. 
(NACA RM L53E06) 



A COLLECTION OF DATA FOR ZERO-LIFT DAMP- 
ING IN ROLL OF WING-BODY COMBINATIONS AS 
DETERMINED WITH ROCKET-POWERED MODELS 
EQUIPPED WITH ROLL-TORQUE NOZZLES. 
David G. Stone. July 1953. 23p. diagrs., tab. 
(NACA RM L53E26) 



22 



(1) AERODYNAMICS 



THE TRANSONIC AERODYNAMIC CHARACTER- 
ISTICS OF STRUCTURALLY RELATED WINGS OF 
LOW ASPECT RATIO HAVING A SPANWISE VARIA- 
TION IN THICKNESS RATIO - TRANSONIC BUMP 
TECHNIQUE. Joseph W. Cleary. April 1954. 
28p. diagrs., photo. (NACA RM A54B18) 



A METHOD FOR THE DESIGN OF SWEPTBACK 
WINGS WARPED TO PRODUCE SPECIFIED FLIGHT 
CHARACTERISTICS AT SUPERSONIC SPEEDS. 
Warren A. Tuckor. 1955. i, 17p. diagrs., tabs. 
(NACA Rept. 1226. Supersedes RM L51F08) 



INVESTIGATIONS AT SUPERSONIC SPEEDS OF 22 
TRIANGULAR WINGS REPRESENTING TWO AIR- 
FOIL SECTIONS FOR EACH OF 11 APEX ANGLES. 
Eugene S. Love. 1955. 11, 60p. diagrs., photos., 
tabs. (NACA Rept. 1238. Supersedes RM L9D07) 



AN ANALYSIS OF ESTIMATED AND EXPERI- 
MENTAL TRANSONIC DOWNWASH CHARACTER- 
ISTICS AS AFFECTED BY PLAN FORM AND THICK- 
NESS FOR WING AND WING- FUSELAGE CONFIG- 
URATIONS. Joseph Weil, George S. Campbell and 
Margaret S. Dlederich. April 1956. 92p. diagrs., 
photos., tabs. (NACA TN 3628. Supersedes 
RM L52I22) 



(1.2.2.2. 1) 
Profiles 



THE HIGH-SPEED AERODYNAMIC EFFECTS OF 
MODIFICATIONS TO THE WING AND WING- 
FUSELAGE INTERSECTION OF AN AIRPLANE 
MODEL WITH THE WING SWEPT BACK 35°. Lee 
E. Boddy and Charles P. Morrill, Jr. February 18, 
1948. 34p. diagrs., photos. (NACA RM A7J02) 



A COMPARISON OF THE EXPERIMENTAL AND 
THEORETICAL LOADING OVER TRIANGULAR 
WINGS IN SIDESLIP AT SUPERSONIC SPEEDS. 
John W. Boyd. May 18, 1951. 58p. diagrs., photo., 
tabs. (NACA RM A51C13) 



AN INVESTIGATION OF FOUR WINGS OF SQUARE 
PLAN FORM AT A MACH NUMBER OF 6.86 IN THE 
LANGLEY 11-PNCH HYPERSONIC TUNNEL. 
Charles H. McLellan, Mitchel H. Bertram, and 
John A. Moore. June 1951. 47p. diagrs., photos. 
(NACA RM L51D17) 



CHARACTERISTICS THROUGHOUT THE SUBSONIC 
SPEED RANGE OF A PLANE WING AND OF A 
CAMBERED AND TWISTED WING, BOTH HAVING 
45° OF SWEEPBACK. Ben H. Johnson, Jr., and 
Harry H. Shibata. July 1951. 122p. diagrs., 
photos. (NACA RM A51D27) 



THE EFFECT ON ZERO-LIFT DRAG OF AN IN- 
DENTED FUSELAGE OR A THICKENED WING-ROOT 
MODIFICATION TO A 45° SWEPTBACK WING-BODY 
CONFIGURATION AS DETERMINED BY FLIGHT 
TESTS AT TRANSONIC SPEEDS. William B. 
Pepper. September 1951. 20p. diagrs., photos., 
2 tabs. (NACA RM L51F15) 



AN INVESTIGATION THROUGHOUT THE SUBSONIC 
SPEED RANGE OF A FULL-SPAN AND A SEMI- 
SPAN MODEL OF A PLANE WING AND OF A 
CAMBERED AND TWISTED WING, ALL HAVING 
45° OF SWEEPBACK. Harry H. Shibata, Angelo 
Bandettini, and Joseph Cleary. June 1952. 65p. 
diagrs., photos. (NACA RM A52D01) 



EFFECT OF CAMBER AND TWIST ON THE STA- 
BILITY CHARACTERISTICS OF MODELS HAVING A 
45° SWEPT WING AS DETERMINED BY THE FREE- 
FALL METHOD AT TRANSONIC SPEEDS. Maurice 
D. White. August 1952. 35p. diagrs., photos., tab. 
(NACARMA52F16) 



TRANSONIC FLIGHT TESTS TO DETERMINE THE 
EFFECT OF THICKNESS RATIO AND PLAN-FORM 
MODIFICATION ON THE ZERO-LIFT DRAG OF A 
45° SWEPTBACK WING. William B. Pepper, Jr., 
and Sherwood Hoffman. August 1952. 24p. diagrs., 
photos., tabs. (NACA RM L52F02a) 



FREE-FLIGHT TESTS AT MACH NUMBERS FROM 
0.8 TO 1.4 TO DETERMINE THE EFFECT ON 
ZERO-LIFT DRAG OF INCREASING THE LEADING- 
EDGE BLUNTNESS OF A 45° SWEPTBACK WING 
HAVING AN NACA 65A009 AIRFOIL. William B. 
Pepper, Jr. August 1952. 15p. diagrs., photos., 
tabs. (NACA RM L52F30) 



AN EXPERIMENTAL INVESTIGATION OF THE 
ZERO-LIFT-DRAG CHARACTERISTICS OF SYM- 
METRICAL BLUNT-TRAILING-EDGE AIRFOILS AT 
MACH NUMBERS FROM 2.7 TO 5.0. Clarence A. 
Syvertson and Hermilo R. Gloria. April 1953. 31p. 
diagrs., photos., tabs. (NACA RM A53B02) 



EFFECT OF REDUCTION IN THICKNESS FROM 6 
TO 2 PERCENT AND REMOVAL OF THE POINTED 
TIPS ON THE SUBSONIC STATIC LONGITUDINAL 
STABILITY CHARACTERISTICS OF A 60° TRIANGU- 
LAR WING IN COMBINATION WITH A FUSELAGE. 
William E. Palmer. August 1953 44p. diagrs., 
photo., tab. (NACA RM L53F24) 



DETERMINATION OF MEAN CAMBER SURFACES 
FOR WINGS HAVING UNIFORM CHORDWISE LOAD- 
ING AND ARBITRARY SPANWISE LOADING IN 
SUBSONIC FLOW. S. Katzoff, M. Frances Faison 
and Hugh C. DuBose. 1954. ii, 17p. diagrs., tab. 
(NACA Rept. 1176. Formerly TN 2908) 



STABILITY CHARACTERISTICS AT LOW SPEED OF 
A VARIABLE -SWEEP AIRPLANE MODEL HAVING 
A PARTIALLY CAMBERED WING WITH SEVERAL 
CHORD-EXTENSION CONFIGURATIONS. Robert E. 
Becht. February 1954. 37p. diagrs., photos. 
(NACA RM L53L14) 



THE TRANSONIC CHARACTERISTICS OF UNSWEPT 
WINGS HAVING ASPECT RATIOS OF 4, SPANWISE 
VARIATIONS IN THICKNESS RATIO, AND VARIA- 
TIONS IN PLAN-FORM TAPER - TRANSONIC- 
BUMP TECHNIQUE. Warren H. Nelson. March 
1954. 29p. diagrs., photo. (NACA RM A53L17) 



23 



(1) AERODYNAMICS 



EFFECTS OF SWEEP AND THICKNESS ON THE 
STATIC LONGITUDINAL AERODYNAMIC CHARAC- 
TERISTICS OF A SERIES OF THIN, LOW-ASPECT- 
RATIO. HIGHLY TAPERED WINGS AT TRANSONIC 
SPEEDS. TRANSONIC-BUMP METHOD. Albert G. 
Few, Jr., and Paul G. Fournier. April 1954. 107p. 
diagrs., photo., tab. (NACA RM L54B25) 



A CORRELATION BY MEANS OF TRANSONIC 
SIMILARITY RULES OF EXPERIMENTALLY DE- 
TERMINED CHARACTERISTICS OF A SERIES OF 
SYMMETRICAL AND CAMBERED WINGS OF 
RECTANGULAR PLAN FORM. John B. McDevitt. 
1955. ii, 23p. diagrs., tabs. (NACA Rept. 1253. 
Supersedes RM A51L17b; RM A53G31) 



THE TRANSONIC CHARACTERISTICS OF 22 
RECTANGULAR, SYMMETRICAL WING MODELS 
OF VARYING ASPECT RATIO AND THICKNESS. 
Warren H. Nelson and John B. McDevitt. June 1955. 
109p. diagrs., photos. (NACA TN 3501. Formerly 
RM ASIA 12) 



THE TRANSONIC CHARACTERISTICS OF 38 
CAMBERED RECTANGULAR WINGS OF VARYING 
ASPECT RATIO AND THICKNESS AS DETERMINED 
BY THE TRANSONIC -BUMP TECHNIQUE. Warren 
H. Nelson and Walter J. Krumm. June 1955. 173p. 
diagrs., photos. (NACA TN 3502. Formerly 
RM A52D11) 



EFFECT OF TRAILING-EDGE THICKNESS ON LIFT 
AT SUPERSONIC VELOCITIES. Dean R. Chapman 
and Robert H. Kester. June 1955. 19p. diagrs. 
(NACA TN 3504. Formerly RM A52D17) 



REDUCTION OF PROFILE DRAG AT SUPERSONIC 
VELOCITIES BY THE USE OF AIRFOIL SECTIONS 
HAVING A BLUNT TRAILING EDGE. Dean R. 
Chapman. September 1955. 29p. diagrs. , photo. 
(NACA TN 3503. Supersedes RM A9H11) 



SUMMARY OF RESULTS OBTAINED Btf 
TRANSONIC -BUMP METHOD ON EFFECTS OF 
PLAN FORM AND THICKNESS ON LIFT AND DRAG 
CHARACTERISTICS OF WINGS AT TRANSONIC 
SPEEDS. Edward C. Polhamus. November 1955. 
33p. diagrs., tab. (NACA TN 3469. Supersedes 
RM L51H30) 



FLIGHT INVESTIGATION AT MACH NUMBERS 
FROM 0.6 TO 1.7 TO DETERMINE DRAG AND 
BASE PRESSURES ON A BLUNT-TRAILING-EDGE 
AIRFOIL AND DRAG OF DIAMOND AND CIRCULAR- 
ARC AIRFOILS AT ZERO LIFT. John D. Morrow 
and Ellis Katz. November 1955. 19p. diagrs., 
photos. (NACA TN 3548. Supersedes RM L50El9a) 



MEASUREMENTS OF THE EFFECT OF TRAILING- 
EDGE THICKNESS ON THE ZERO-LIFT DRAG OF 
THIN LOW-ASPECT-RATIO WINGS. John D. 
Morrow. November 1955. lip. diagrs., photo. 
(NACA TN 3550. Supersedes RM L50F26) 



THE TRANSONIC CHARACTERISTICS OF 36 SYM- 
METRICAL WINGS OF VARYING TAPER, ASPECT 
RATIO, AND THICKNESS AS DETERMINED BY THE 
TRANSONIC -BUMP TECHNIQUE. Warren H. 
Nelson, Edwin C. Allen, and Walter J. Krumm. 
December 1955. 131p. diagrs., photo. 
(NACA TN 3529. Supersedes RM A 5 3129) 



WIND-TUNNEL INVESTIGATION OF THE EFFECT 
OF CLIPPING THE TIPS OF TRIANGULAR WINGS 
OF DIFFERENT THICKNESS, CAMBER, AND AS- 
PECT RATIO - TRANSONIC BUMP METHOD. 
Horace F. Emerson. June 1956. 183p. diagrs., 
photo., tabs. (NACA TN 3671. Supersedes 
RM A53L03) 



(1.2.2.2.2) 
Aspect Ratio 

FREE-FLIGHT INVESTIGATION OF CONTROL EF- 
FECTIVENESS OF FULL-SPAN, 0.2-CHORD PLAIN 
AILERONS AT HIGH SUBSONIC, TRANSONIC, AND 
SUPERSONIC SPEEDS TO DETERMINE SOME EF- 
FECTS OF WING SWEEPBACK, TAPER, ASPECT 
RATIO, AND SECTION-THICKNESS RATIO. Carl A. 
Sandahl. August 13, 1947. 16p. diagrs., photos., 
tab. (NACA RM L7F30) 



LIFT AND PITCHING-MOMENT INTERFERENCE 
BETWEEN A POINTED CYLINDRICAL BODY AND 
TRIANGULAR WINGS OF VARIOUS ASPECT RATIOS 
AT MACH NUMBERS OF 1.50 AND 2.02. Jack N. 
Nielsen, Elliott D. Katzen, and Kenneth K. Tang. 
September 12, 1950. 53p. diagrs., photos., tabs. 
(NACA RM A50F06) 



AERODYNAMIC CHARACTERISTICS INCLUDING 
PRESSURE DISTRIBUTIONS OF A FUSELAGE AND 
THREE COMBINATIONS OF THE FUSELAGE WITH 
SWEPT-BACK WINGS AT HIGH SUBSONIC SPEEDS. 
Fred B. Sutton and Andrew Martin. February 6, 
1951. 117p. diagrs., photos., tabs. 
(NACA RM A50J26a) 



DRAG INTERFERENCE BETWEEN A POINTED 
CYLINDRICAL BODY AND TRIANGULAR WINGS OF 
VARIOUS ASPECT RATI06 AT MACH NUMBERS OF 
1.50 AND 2.02. Elliott D. Katzen and George E. 
Kaattari. May 23, 1951. 45p. diagrs., photos., tabs. 
(NACA RM A51C27) 



RECENT EXPERIMENTAL FLUTTER STUDIES. 
Arthur A. Regier and Dennis J. Martin. June 12, 
1951. 18p. diagrs. (NACA RM L51F11) 



WIND-TUNNEL INVESTIGATION OF THE AERODY- 
NAMIC CHARACTERISTICS IN PITCH OF WING- 
FUSELAGE COMBINATIONS AT HIGH SUBSONIC 
SPEEDS. ASPECT-RATIO SERIES. Richard E. 
Kuhn and James W. Wiggins. April 1952. 42p. 
diagrs., photos., tab. (NACA RM L52A29) 



PRELIMINARY RESULTS OF HORIZONTAL -TAIL 
LOAD MEASUREMENTS OF THE BELL X-5 RE- 
SEARCH AIRPLANE. John T. Rogers and Angel H. 
Dunn. August 15, 1952. 22p. diagrs., photos., 
tabs. (NACA RM L52G14) 



24 



(1) AERODYNAMICS 



INVESTIGATION OF THE LOW-SPEED AERO- 
DYNAMIC CHARACTERISTICS OF A VARIABLE - 
SWEEP AIRPLANE MODEL WITH A WING HAVING 
PARTIAL-SPAN CAMBERED- LEADING-EDGE 
MODIFICATIONS. Robert E. Becht and Andrew L, 
Byrnes, Jr. September 1952. 47p. diagrs., photos. 
(NACA RM L52G08a) 



WIND-TUNNEL INVESTIGATION OF THE STATIC 
LATERAL STABILITY CHARACTERISTICS OF 
WING-FUSELAGE COMBINATIONS AT HIGH SUB- 
SONIC SPEEDS. ASPECT-RATIO SERIES. Paul G. 
Fournier and Andrew L. Byrnes, Jr. February 1953. 
26p. diagrs., photos. (NACA RM L52L18) 



INVESTIGATIONS OF THE DAMPING IN ROLL OF 
SWEPT AND TAPERED WINGS AT SUPERSONIC 
SPEEDS. Russell W. McDearmon and Harry S. 
Heinke, Jr. March 1953. 35p. diagrs., photos., 
tab. (NACA RM L53A13) 



EXPERIMENTAL INVESTIGATION OF THE EF- 
FECTS OF PLAN-FORM TAPER ON THE AERO- 
DYNAMIC CHARACTERISTICS OF SYMMETRICAL 
UNSWEPT WINGS OF VARYING ASPECT RATIO. 
Edwin C. Allen. May 1953. 53p. diagrs., photos., 
tab. (NACA RM A53C19) 



THE LOW -SPEED LIFT AND DRAG CHARACTER- 
ISTICS OF A SERIES OF AIRPLANE MODELS 
HAVING TRIANGULAR OR MODIFIED TRIANGULAR 
WINGS. David Graham. June 1953. 49p. diagrs., 
photo., tabs. (NACA RM A53D14) 



EFFECT OF REDUCTION IN THICKNESS FROM 6 
TO 2 PERCENT AND REMOVAL OF THE POINTED 
TIPS ON THE SUBSONIC STATIC LONGITUDINAL 
STABILITY CHARACTERISTICS OF A 60° TRIANGU- 
LAR WING IN COMBINATION WITH A FUSELAGE. 
William E. Palmer. August 1953. 44p. diagrs., 
photo., tab. (NACA RM L53F24) 



A STUDY OF THE PROBLEM OF DESIGNING AIR- 
PLANES WITH SATISFACTORY INHERENT DAMP- 
ING OF THE DUTCH ROLL OSCILLATION. John P. 
Campbell and Marion O. McKinney, Jr. 1954. ii, 
18p. diagrs., tabs. (NACA Rept. 1199. Super- 
sedes TN 3035) 



STABILITY CHARACTERISTICS AT LOW SPEED OF 
A VARIABLE -SWEEP AIRPLANE MODEL HAVING 
A PARTIALLY CAMBERED WING WITH SEVERAL 
CHORD- EXTENSION CONFIGURATIONS. Robert E. 
Becht. February 1954. 37p. diagrs., photos. 
(NACA RM L53L14) 



EFFECTS OF SWEEP AND THICKNESS ON THE 
STATIC LONGITUDINAL AERODYNAMIC CHARAC- 
TERISTICS OF A SERIES OF THIN, LOW-ASPECT- 
RATIO, HIGHLY TAPERED WINGS AT TRANSONIC 
SPEEDS. TRANSONIC-BUMP METHOD. Albert G. 
Few, Jr., and Paul G. Fournier. April 1954. 107p. 
diagrs., photo., tab. (NACA RM L54B25) 



CALCULATED SPANWISE LIFT DISTRIBUTIONS, 
INFLUENCE FUNCTIONS, AND INFLUENCE COEF- 
FICIENTS FOR UNSWEPT WINGS IN SUBSONIC 
FLOW. Franklin W. Diederich and Martin Zlotnick. 
1955. ii, 69p. diagrs., tabs. (NACA Rept. 1228. 
Supersedes TN 3014) 



A CORRELATION BY MEANS OF TRANSONIC 
SIMILARITY RULES OF EXPERIMENTALLY DE- 
TERMINED CHARACTERISTICS OF A SERIES OF 
SYMMETRICAL AND CAMBERED WINGS OF 
RECTANGULAR PLAN FORM. John B. McDevitt. 
1955. il, 23p. diagrs., tabs. (NACA Rept. 1253. 
Supersedes RM A51L17b; RM A53G31) 



WING-LOAD MEASUREMENTS OF THE BELL X-5 
RESEARCH AIRPLANE AT A SWEEP ANGLE OF 
58.7°. Richard D. Banner, Robert D. Reed, and 
William L. Marcy. April 1955. 22p. diagrs., 
photo., tab. (NACA RM H55A11) 



THE TRANSONIC CHARACTERISTICS OF 22 
RECTANGULAR, SYMMETRICAL WING MODELS 
OF VARYING ASPECT RATIO AND THICKNESS. 
Warren H. Nelson and John B. McDevitt. June 1955. 
109p. diagrs., photos. (NACA TN 3501. Formerly 
RM A51A12) 



THE TRANSONIC CHARACTERISTICS OF 38 
CAMBERED RECTANGULAR WINGS OF VARYING 
ASPECT RATIO AND THICKNESS AS DETERMINED 
BY THE TRANSONIC -BUMP TECHNIQUE. Warren 
H. Nelson and Walter J. Krumm. June 1955. 173p. 
diagrs., photos. (NACA TN 3502. Formerly 
RM A52D11) 



EFFECT OF TRAILING-EDGE THICKNESS ON LIFT 
AT SUPERSONIC VELOCITIES. Dean R. Chapman 
and Robert H. Kester. June 1955. 19p. diagrs. 
(NACA TN 3504. Formerly RM A52D17) 



FLOW STUDIES ON FLAT-PLATE DELTA WINGS 
AT SUPERSONIC SPEED. William H. Michael, Jr. 
July 1955. 40p. diagrs., photos. {NACA TN 3472) 



SUMMARY OF RESULTS OF A WIND-TUNNEL 
INVESTIGATION OF NINE RELATED HORIZONTAL 
TAILS. Jules B. Dods, Jr. and Bruce E. Tinling. 
July 1955. 105p. diagrs., 2 tabs. (NACA TN 3497. 
Formerly RM A51G31a) 



CORRECTION OF ADDITIONAL SPAN LOADINGS 
COMPUTED BY THE WEISSINGER SEVEN-POINT 
METHOD FOR MODERATELY TAPERED WINGS 
OF HIGH ASPECT RATIO. John DeYoung and 
Walter H. Barling, Jr. July 1955. 31p. diagrs. 
(NACA TN 3500) 



WIND-TUNNEL INVESTIGATION AT LOW SPEED 
OF EFFECT OF SIZE AND POSITION OF CLOSED 
AIR DUCTS ON STATIC LONGITUDINAL AND 
STATIC LATERAL STABILITY CHARACTERISTICS 
OF UNSWEPT -MIDWING MODELS HAVING WINGS 
OF ASPECT RATIO 2, 4, AND 6. Byron M. Jaquet 
and James L. Williams. September 1955. 45p. 
diagrs., photos., tabs. (NACA TN 3481) 



25 



(1) AERODYNAMICS 



MEASUREMENTS OF THE EFFECTS OF FINITE 
SPAN ON THE PRESSURE DISTRIBUTION OVER 
DOUBLE-WEDGE WINGS AT MACH NUMBERS 
NEAR SHOCK ATTACHMENT. Walter G. Vincenti. 
September 1955. 50p. diagrs. (NACA TN 3522) 



CALCULATED SPANWISE LIFT DISTRIBUTIONS 
AND AERODYNAMIC INFLUENCE COEFFICIENTS 
FOR SWEPT WINGS IN SUBSONIC FLOW. 
Franklin W. Diederich and Martin Zlotnick. 
October 1955. 173p. diagrs., tabs. (NACA 
TN 3476) 



SUMMARY OF RESULTS OBTAINED BY 
TRANSONIC-BUMP METHOD ON EFFECTS OF 
PLAN FORM AND THICKNESS ON LIFT AND DRAG 
CHARACTERISTICS OF WINGS AT TRANSONIC 
SPEEDS. Edward C. Polhamus. November 1955. 
33p. diagrs., tab. (NACA TN 3469. Supersedes 
RM L51H30) 



THE TRANSONIC CHARACTERISTICS OF 36 SYM- 
METRICAL WINGS OF VARYING TAPER, ASPECT 
RATIO, AND THICKNESS AS DETERMINED BY THE 
TRANSONIC -BUMP TECHNIQUE. Warren H. 
Nelson, Edwin C. Allen, and Walter J, Krumm. 
December 1955. 131p. diagrs., photo. 
(NACA TN 3529. Supersedes RM A53I29) 



THEORETICAL SPAN LOAD DISTRIBUTIONS AND 
ROLLING MOMENTS FOR SIDESLIPPING WINGS 
OF ARBITRARY PLAN FORM IN INCOMPRESSIBLE 
FLOW. M. J. Queijo. December 1955. 45p. 
diagrs. (NACA TN 3605) 



FLOW STUDIES ON DROOP ED -LEADING -EDGE 
DELTA WINGS AT SUPERSONIC SPEED. William 
H. Michael, Jr. January 1956. 29p. diagrs., 
photos. (NACA TN 3614) 



PRELIMINARY STUDY OF SOME FACTORS WHICH 
AFFECT THE STALL-FLUTTER CHARACTER- 
ISTICS OF THIN WINGS. A. Gerald Rainey. March 
1956. 33p. diagrs., photo., tab. (NACA TN 3622. 
Supersedes RM L52D08) 



AN ANALYSIS OF ESTIMATED AND EXPERI- 
MENTAL TRANSONIC DOWNWASH CHARACTER- 
ISTICS AS AFFECTED BY PLAN FORM AND THICK- 
NESS FOR WING AND WING* FUSELAGE CONFIG- 
URATIONS. Joseph Weil, George S. Campbell and 
Margaret S. Diederich. April 1956. 92p. diagrs., 
photos., tabs. (NACA TN 3628. Supersedes 
RM L52I22) 



APPROXIMATE INDICIAL LIFT FUNCTIONS FOR 
SEVERAL WINGS OF FINITE SPAN IN INCOM- 
PRESSIBLE FLOW AS OBTAINED FROM OSCILLA- 
TORY LIFT COEFFICIENTS. Joseph A. Drischler. 
May 1956. 26p. diagrs., tab. (NACA TN 3639) 



STATIC LONGITUDINAL AND LATERAL STABILITY 
CHARACTERISTICS AT LOW SPEED OF UNSWEPT- 
MIDWING MODELS HAVING WINGS WITH AN 
ASPECT RATIO OF 2, 4, OR 6. Walter D. Wolhart 
and David F. Thomas, Jr. May 1956. 41p. 
diagrs., photos., tabs. (NACA TN 3649) 



ON THE RANGE OF APPLICABILITY OF THE 
TRANSONIC AREA RULE. John R. Spreiter. 
May 1956. 21p. diagrs. (NACA TN 3673. Super- 
sedes RM A54F28) 



WIND-TUNNEL INVESTIGATION OF THE EFFECT 
OF CLIPPING THE TIPS OF TRIANGULAR WINGS 
OF DIFFERENT THICKNESS, CAMBER, AND AS- 
PECT RATIO - TRANSONIC BUMP METHOD. 
Horace F. Emerson. June 1956. 183p. diagrs., 
photo., tabs. (NACA TN 3671. Supersedes 
RM A53L03) 



FLIGHT TESTS AT SUPERSONIC SPEEDS TO 
DETERMINE THE EFFECT OF TAPER ON THE 
ZERO-LIFT DRAG OF SWEPTBACK LOW-ASPECT- 
RATIO WINGS. Murray Pittel. June 1956. 20p. 
diagrs., photos. (NACA TN 3697. Supersedes 
RM L50F30a) 



PRELIMINARY WIND-TUNNEL TESTS OF TRIAN- 
GULAR AND RECTANGULAR WINGS IN STEADY 
ROLL AT MACH NUMBERS OF 1.62 AND 1.92. 
Clinton E. Brown and Harry S. Helnke, Jr. 
June 1956. 36p. diagrs., tabs. 
(NACA TN 3740. Supersedes RM L8L30) 



(1.2.2.2. 3) 

Sweep 



FREE-FLIGHT INVESTIGATION OF CONTROL EF- 
FECTIVENESS OF FULL-SPAN, 0.2-CHORD PLAIN 
AILERONS AT HIGH SUBSONIC, TRANSONIC, AND 
SUPERSONIC SPEEDS TO DETERMINE SOME EF- 
FECTS OF WING SWEEFBACK, TAPER, ASPECT 
RATIO, AND SECTION-THICKNESS RATIO. Carl A. 
Sandahl. August 13, 1947. 16p. diagrs., photos., 
tab. (NACA RM L7F30) 



THE HIGH-SPEED AERODYNAMIC EFFECTS OF 
MODIFICATIONS TO THE WING AND WING- 
FUSELAGE INTERSECTION OF AN AIRPLANE 
MODEL WITH THE WING SWEPT BACK 35°. Lee 
E. Boddy and Charles P. Morrill, Jr. February 18, 
1948. 34p. diagrs., photos. {NACA RM A7J02) 



HIGH-SPEED STABILITY AND CONTROL CHARAC- 
TERISTICS OF A FIGHTER AIRPLANE MODEL 
WITH ASWEPT-BACK WING AND TAIL. Charles 
P. Morrill, Jr., and Lee E. Boddy. April 14, 1948. 
47p. diagrs., photos. (NACA RM A7K28) 



LONGITUDINAL -STABILITY INVESTIGATION OF 
HIGH-LIFT AND STALL-CONTROL DEVICES ON A 
52° SWEPTBACK WING WITH AND WITHOUT FUSE- 
LAGE AND HORIZONTAL TAIL AT A REYNOLDS 
NUMBER OF 6.8 x 10 6 . Gerald V. Foster and 
James E. Fitzpatrick. December 20, 1948. 41p. 
diagrs., photos., tabs. (NACA RM L8I08) 



HIGH-SPEED WIND-TUNNEL INVESTIGATION OF 
A SWEPTBACK WING WITH AN ADDED TRIANGU- 
LAR AREA AT THE CENTER. Beverly Z. Henry, 
Jr. January 14, 1949. 24p. diagrs., tabs. 
(NACA RM L8J12) 



26 



(1) AERODYNAMICS 



AERODYNAMIC STUDY OF A WING- FUSELAGE 
COMBINATION EMPLOYING A WING SWEPT BACK 
63°. - AERODYNAMIC CHARACTERISTICS IN 
SIDESLIP OF A LARGE-SCALE MODEL HAVING A 
63° SWEPT-BACK VERTICAL TAIL. Gerald M. 
McCormack. October 7, 1949. 26p. diagrs., 
photos. (NACA RM A9F14) 



A TRANSONIC-WING INVESTIGATION IN THE 
LANGLEY 8-FOOT HIGH-SPEED TUNNEL AT HIGH 
SUBSONIC MACH NUMBERS AND AT A MACH 
NUMBER OF 1.2. WING-FUSELAGE CONFIGURA- 
TION WITH A WING OF 45° SWEEPBACK, ASPECT 
RATIO 4, TAPER RATIO 0.6, AND NACA 65A006 
AIRFOIL SECTION. Robert S. Osborne. 
October 10, 1950. 49p. diagrs., photos. 
(NACA RM L50H08) 



A TRANSONIC WING INVESTIGATION IN THE 
LANGLEY 8-FOOT HIGH-SPEED TUNNEL AT HIGH 
SUBSONIC MACH NUMBERS AND AT A MACH 
NUMBER OF 1.2. WING-FUSELAGE CONFIGURA- 
TION HAVING A WING OF 35° SWEEPBACK, AS- 
PECT RATIO 4, TAPER RATIO 0.6, AND NACA 
65A006 AIRFOIL SECTION. Beverly Z. Henry, Jr. 
November 15, 1950. 40p. diagrs., photo., tab. 
(NACA RML50J09) 



HORIZONTAL -TAIL EFFECTIVENESS AND DOWN- 
WASH SURVEYS FOR TWO 47.7° SWEPTBACK 
WING-FUSELAGE COMBINATIONS WITH ASPECT 
RATIOS OF 5.1 AND 6.0 AT A REYNOLDS NUMBER 
OF 6.0 x 10 6 . Reino J. Salmi. January 12, 1951. 
65p. diagrs., photos., 2 tabs. (NACA RM L50K06) 



A TRANSONIC -WING INVESTIGATION IN THE 
LANGLEY 8-FOOT HIGH-SPEED TUNNEL AT HIGH 
SUBSONIC MACH NUMBERS AND AT A MACH NUM- 
BER OF 1.2. WING-FUSELAGE CONFIGURATION 

HAVING A WING OF 60° SWEEPBACK, ASPECT 
RATIO 4, TAPER RATIO 0.6, AND NACA 65A00b 
AIRFOIL SECTION. Raymond B. Wood and Frank F. 
Fleming. January 24, 1951. 43p. diagrs., photo. 
(NACA RM L50J25) 



AERODYNAMIC CHARACTERISTICS INCLUDING 
PRESSURE DISTRIBUTIONS OF A FUSELAGE AND 
THREE COMBINATIONS OF THE FUSELAGE WITH 
SWEPT-BACK WINGS AT HIGH SUBSONIC SPEEDS. 
Fred B. Sutton and Andrew Martin. February 6, 
1951. 117p. diagrs., photos., tabs. 
(NACA RM A50J26a) 



LOW-SPEED LONGITUDINAL AND WAKE AIR- 
FLOW CHARACTERISTICS AT A REYNOLDS NUM- 
BER OF 6.0 x 10 6 OF A 52° SWEPTBACK WING 
EQUIPPED WITH VARIOUS SPANS OF LEADING- 
EDGE AND TRAILING-EDGE FLAPS, A FUSELAGE, 
AND A HORIZONTAL TAIL AT VARIOUS VERTICAL 
POSITIONS. Roland F. Griner and Gerald V. Foster. 
February 28, 1951. 66p. diagrs., photo., 3 tabs. 
(NACA RM L50K29) 



SOME EXPERIMENTS ON THE FLUTTER OF 
SWEPTBACK CANTILEVER WING MODELS AT 
MACH NUMBER 1.3. W. J. Tuovila. March 15, 
1951. lOp. diagrs., tab. (NACA RM L51A11) 



TESTS IN THE AMES 40- BY 80-FOOT WIND TUN- 
NEL OF AN AIRPLANE CONFIGURATION WITH AN 
ASPECT RATIO 2 TRIANGULAR WING AND AN 
ALL-MOVABLE HORIZONTAL TAIL- 
LONGITUDINAL CHARACTERISTICS. David Graham 
and David G. Koenig. April 23, 1951. 35p. diagrs., 
photo., 3 tabs. (NACA RM A51B21) 

SOME EFFECTS OF SPANWISE AILERON LOCA- 
TION AND WING STRUCTURAL RIGIDITY ON THE 
ROLLING EFFECTIVENESS OF 0.3-CHORD FLAP- 
TYPE AILERONS ON A TAPERED WING HAVING 
63° SWEEPBACK AT THE LEADING EDGE AND 
NACA 64A005 AIRFOIL SECTIONS, H. Kurt 
Strass, E. M. Fields, and Eugene D. Schult. 
June 1951. 25p. diagrs., photo., tab, 
(NACA RM L51D18a) 

COMPARISON OF ZERO-LIFT DRAG DETERMINED 
BY FLIGHT TESTS AT TRANSONIC SPEEDS OF 
PYLON, UNDERSLUNG, AND SYMMETRICALLY 
MOUNTED NACELLES AT 40 PERCENT SEMISPAN 
OF A 45° SWEPTBACK WING AND BODY COMBINA- 
TION. Sherwood Hoffman. June 1951. 18p. diagrs., 
photos., tabs. (NACA RM L51D26) 



AERODYNAMIC CHARACTERISTICS OF FOUR 
WINGS OF SWEEPBACK ANGLES 0°, 35°, 45°, AND 
60°, NACA 65A006 AIRFOIL SECTION, ASPECT 
RATIO 4, AND TAPER RATIO 0.6 IN COMBINATION 
WITH A FUSELAGE AT HIGH SUBSONIC MACH 
NUMBERS AND AT A MACH NUMBER OF 1.2. 
Arvo A. Luoma. June 6, 1951. 59p. diagrs., photo., 
tab. (NACA RM L51D13) 



RECENT EXPERIMENTAL FLUTTER STUDIES. 
Arthur A. Regier and Dennis J. Martin. June 12, 
1951. 18p. diagrs. (NACA RM L51F11) 



LOW-SPEED LONGITUDINAL AND WAKE AIR- 
FLOW CHARACTERISTICS AT A REYNOLDS NUM- 
BER OF 5.5 x 10 6 OF A CIRCULAR-ARC 52° 
SWEPTBACK WING WITH A FUSELAGE AND A 
HORIZONTAL TAIL AT VARIOUS VERTICAL POSI- 
TIONS. Gerald V. Foster and Roland F. Griner. 
Jvyie 19, 1951. 44p. diagrs., tabs. 
(NACA RM L51C30) 



CHARACTERISTICS THROUGHOUT THE SUBSONIC 
SPEED RANGE OF A PLANE WING AND OF A 
CAMBERED AND TWISTED WING, BOTH HAVING 
45° OF SWEEPBACK. Ben H. Johnson, Jr., and 
Harry H. Shibata. July 1951. 122p. diagrs., 
photos. (NACA RM A51D27) 



INVESTIGATION OF THE EFFECTS OF TWIST AND 
CAMBER ON THE AERODYNAMIC CHARACTER- 
ISTICS OF A 50° 38' SWEPTBACK WING OF AS- 
PECT RATIO 2.98. TRANSONIC -BUMP METHOD. 
Kenneth P. Spreemann and William J. Alford, Jr. 
August 1951. 33p. diagrs., photos., tab. 
(NACA RML51C16) 



TRANSONIC -WING INVESTIGATION IN THE 
LANGLEY 8-FOOT HIGH-SPEED TUNNEL AT HIGH 
SUBSONIC MACH NUMBERS AND AT A MACH NUM- 
BER OF 1.2. ANALYSIS OF PRESSURE DISTRIBU- 
TION OF WING-FUSELAGE CONFIGURATION HAV- 
ING A WING OF 45° SWEEPBACK, ASPECT RATIO 
4, TAPER RATIO 0.6, AND NACA 65A006 AIRFOIL 
SECTION. Donald L. Loving and Bruce B. 
Estabrooks. September 1951. 132p. diagrs., photos. 
(NACA RM L51F07) 



27 



(1) AERODYNAMICS 



COMPARISON OF ZERO-LIFT DRAGS DETER- 
MINED BY FLIGHT TESTS AT TRANSONIC SPEEDS 
OF SYMMETRICALLY MOUNTED NACELLES IN 
VARIOUS CHORDWISE POSITIONS AT THE WING 
TIP OF A 45° SWEPTBACK WING AND BODY 
COMBINATION. William B. Pepper, Jr., and 
Sherwood Hoffman. September 1951. 16p. diagrs., 
photos. (NACA RM L51F13) 



THE EFFECT ON ZERO-LIFT DRAG OF AN IN- 
DENTED FUSELAGE OR A THICKENED WING-ROOT 
MODIFICATION TO A 45° SWEPTBACK WING -BODY 
CONFIGURATION AS DETERMINED BY FLIGHT 
TESTS AT TRANSONIC SPEEDS. William B. 
Pepper. September 1951. 20p. diagrs., photos., 
2 tabs. (NACA RM L51F15) 



TESTS IN THE AMES 40- BY 80-FOOT WIND TUN- 
NEL OF AN AIRPLANE CONFIGURATION WITH AN 
ASPECT RATIO 4 TRIANGULAR WING AND AN 
ALL-MOVABLE HORIZONTAL TAIL - LONGITUDI- 
NAL CHARACTERISTICS. David Graham and 
David G. Koenig. October 1951. 27p. diagrs., 
photo., 4 tabs. (NACA RM A51H10a) 



SOME EFFECTS OF FUSELAGE INTERFERENCE, 
WING INTERFERENCE AND SWEEPBACK ON THE 
DAMPING IN ROLL OF UNTAPEREi. /INGS AS DE- 
TERMINED BY TECHNIQUES EMPLOYING 
ROCKET-PROPELLED VEHICLES. William M. 
Bland, Jr., and Albert E. Dietz. October 1951. 27p. 
diagrs,, photos= (NACA RM L51D25* 



ROLLING EFFECTIVENESS OF ALL-MOVABLE 
WINGS AT SMALL ANGLES OF INCIDENCE AT 
MACH NUMBERS FROM 0.6 TO 1.6. H. Kurt 
Strass and Edward T. Marley. October 1951. 16p. 
diagrs., photo., tab. (NACA RM L51H03) 



DYNAMIC STABILITY AND CONTROL CHARACTER- 
ISTICS OF A DELTA -WING VERTICALLY RISING 
AIRPLANE MODEL IN TAKE-OFFS, LANDINGS, 
AND HOVERING FLIGHT. Powell M. Lovell, Jr., 
William R. Bates and Charles C. Smith, Jr. 
October 1951. 14p. diagrs., photo., tab. (NACA 
RM L5lH13a) 



DAMPING IN ROLL OF STRAIGHT AND 45° SWEPT 
WINGS OF VARIOUS TAPER RATIOS DETERMINED 
AT HIGH SUBSONIC, TRANSONIC, AND SUPER- 
SONIC SPEEDS WITH ROCKET-POWERED 
MODELS. E. Claude Sanders, Jr. October 1951. 
15p. diagrs. (NACA RM L51H14) 



EFFECT OF VERTICAL LOCATION OF A HORIZON- 
TAL TAIL ON THE STATIC LONGITUDINAL STA- 
BILITY CHARACTERISTICS OF A 45° SWEPTBACK- 
WING - FUSELAGE COMBINATION OF ASPECT 
RATIO 8 AT A REYNOLDS NUMBER OF 4.0 x 10 6 . 
Relno J. Salmi and William A. Jacques. January 
1952. 42p. diagrs., photos. (NACA RM LSI J08) 



TRANSONIC FLIGHT TESTS TO DETERMINE 
ZERO-LIFT DRAG AND PRESSURE RECOVERY OF 
NACELLES LOCATED AT THE WING TIPS ON A 
45 SWEPTBACK WING AND BODY COMBINATION. 
Sherwood Hoffman and William B. Pepper, Jr. 
January 1952. 21p. diagrs., photos., tabs. 
(NACA RM L51K02) 



TESTS IN THE AMES 40- BY 80-FOOT WIND TUN- 
NEL OF AN AIRPLANE CONFIGURATION WITH AN 
ASPECT RATIO 2 TRIANGULAR WING AND AN 
ALL-MOVABLE HORIZONTAL TAIL - LATERAL 
CHARACTERISTICS. David Graham and David G. 
Koenig. February 1952. 38p. diagrs., 2 tabs. 
(NACA RM A51L03) 



WIND-TUNNEL INVESTIGATION AT LOW SPEED OF 
A TWISTED AND CAMBERED WING SWEPT BACK 
63° WITH VORTEX GENERATORS AND FENCES. 
James A. Weiberg and George B. McCullough. 
March 1952. 45p. diagrs., photos., 3 tabs. 
(NACA RM A52A17) 



SOME WIND-TUNNEL RESULTS OF AN INVESTIGA- 
TION OF THE FLUTTER OF SWEPTBACK- AND 
TRIANGULAR -WING MODELS AT MACH NUMBER 
1.3. W. J. Tuovila. May 1952. 12p. diagrs., tab. 
(NACARM L52C13) 



THE EFFECTS OF REYNOLDS NUMBER AT MACH 
NUMBERS UP TO 0.94 ON THE LOADING ON A 35° 
SWEPTBACK WING HAVING NACA 65iA012 
STREAMWISE SECTIONS. Bruce E. Tinling and 
Armando E. Lopez, June 1952. 115p. diagrs., 
photos., tabs. (NACA RM A52B20) 



AN INVESTIGATION THROUGHOUT THE SUBSONIC 
SPEED RANGE OF A FULL-SPAN AND A SEMI- 






niT A T5T 



v Aiiu rtiu-» 



DFA 



CAMBERED AND TWISTED WING, ALL HAVING 
45° OF SWEEPBACK. Harry H. Shibata, Angelo 
Bandettini, and Joseph Cleary. June 1952. 65p. 
diagrs., photos. (NACA RM A52D01) 



A STUDY OF THE FLOW OVER A 45° SWEPTBACK 
WING-FUSELAGE COMBINATION AT TRANSONIC 
MACH NUMBERS. Richard T. Whitcomb and 
Thomas C. Kelly. June 1952. 60p. diagrs., 
photos. (NACA RM L52D01) 



WIND-TUNNEL INVESTIGATION OF THE AERO- 
DYNAMIC CHARACTERISTICS IN PITCH OF WING- 
FUSELAGE COMBINATIONS AT HIGH -SUBSONIC 
SPEEDS. SWEEP SERIES. James W. Wiggins and 
Richard E. Kuhn. July 1952. 41p. diagrs., photos. 
(NACA RM L52D18) 



RESULTS OF TWO EXPERIMENTS ON FLUTTER 
OF HIGH-ASPECT-RATIO SWEPT WINGS IN THE 
TRANSONIC SPEED RANGE. W. T. Lauten, Jr., 
and Burke R. O'Kelly. July 1952. 22p. diagrs., 
photos., tabs. (NACA RM L52D24b) 



PRELIMINARY RESULTS OF HORIZONTAL -TAIL 
LOAD MEASUREMENTS OF THE BELL X-5 RE- 
SEARCH AIRPLANE. John T. Rogers and Angel H. 
Dunn. August 15, 1952. 22p, diagrs., photos., 
tabs. (NACA RM L52G14) 



THE LONGITUDINAL CHARACTERISTICS AT MACH 
NUMBERS UP TO 0.92 OF A CAMBERED AND 
TWISTED WING HAVING 40° OF SWEEPBACK AND 
AN ASPECT RATIO OF 10. George G. Edwards, 
Bruce E. Tinling, and Arthur C. Ackerman. 
September 1952. 71p. diagrs,, photos., tab. 
(NACA RM A52F18) 



28 



(1) AERODYNAMICS 



THE USE OF LEADING-EDGE AREA SUCTION TO 
INCREASE THE MAXIMUM LIFT COEFFICIENT OF 
A 35° SWEPT-BACK WING. Curt A. Holzhauserand 
Robert K. Martin. September 1952. 37p. diagrs., 
photo., 3 tabs. (NACA RM A52G17) 



INVESTIGATION OF THE LOW-SPEED AERO- 
DYNAMIC CHARACTERISTICS OF A VARIABLE - 
SWEEP AIRPLANE MODEL WITH A WING HAVING 
PARTIAL-SPAN CAMBERED-LEADING-EDGE 
MODIFICATIONS. Robert E. Becht and Andrew L. 
Byrnes, Jr. September 1952. 47p. diagrs., photos. 
(NACA RM L52G08a) 



THE EFFECTS OF SWEEPBACK ON LONGITUDINAL 
CHARACTERISTICS OF A 1/30-SCALE SEMISPAN 
MODEL OF THE BELL X-5 AIRPLANE AS DETER- 
MINED FROM NACA WING-FLOW TESTS AT 
TRANSONIC SPEEDS. Joseph J. Kolnick and 
Robert M. Kennedy. November 1952. 48p. diagrs., 
photos., tab. (NACA RM L52I23) 



EFFECTS OF TWIST AND CAMBER, FENCES, AND 
HORIZONTAL-TAIL HEIGHT ON THE LOW-SPEED 
LONGITUDINAL STABILITY CHARACTERISTICS OF 
A WING- FUSELAGE COMBINATION WITH A 45° 
SWEPTBACK WING OF ASPECT RATIO 8 AT A 
REYNOLDS NUMBER OF 4.0 x 10 6 . Gerald V. 
Foster. December 1952. 3 Op. diagrs., photo. 
(NACA RM L52J03) 



LONGITUDINAL-CONTROL EFFECTIVENESS AND 
DOWNWASH CHARACTERISTICS AT TRANSONIC 
SPEEDS OF A 1/30-SCALE SEMISPAN MODEL OF 
THE BELL X-5 AIRPLANE AS DETERMINED BY 
THE NACA WING-FLOW METHOD. Norman S. 
Silsby and Garland J. Morris. January 1953. 48p. 
diagrs., photos., 2 tabs. (NACA RM L52K12) 



TESTS IN THE AMES 40- BY 80- FOOT WIND TUN- 
NEL OF AN AIRPLANE MODEL WITH AN ASPECT 
RATIO 4 TRIANGULAR WING AND AN ALL- 
MOVABLE HORIZONTAL TAIL - HIGH-LIFT DE- 
VICES AND LATERAL CONTROLS. Ralph W. 
Franks. February 1953. 45p. diagrs., photo., 2 
tabs. (NACA RM A52K13) 



TESTS IN THE AMES 40- BY 80 -FOOT WIND TUN- 
NEL OF TWO AIRPLANE MODELS HAVING AS- 
PECT RATIO 2 TRAPEZOIDAL WINGS OF TAPER 
RATIOS 0.33 AND 0.20. Ralph W. Franks. 
February 1953. 56p. diagrs., photos., 3 tabs. 
(NACA RM A52L16) 



PRELIMINARY RESULTS OF STABILITY AND CON- 
TROL INVESTIGATION OF THE BELL X-5 RE- 
SEARCH AIRPLANE. Thomas W. Finch and Donald 
W. Briggs. February 1953. 35p. diagrs., photos., 
tabs. (NACA RM L52K18b) 



WIND-TUNNEL INVESTIGATION OF THE STATIC 
LATERAL STABILITY CHARACTERISTICS OF 
WING-FUSELAGE COMBINATIONS AT HIGH SUB- 
SONIC SPEEDS. ASPECT-RATIO SERIES. Paul G. 
Fournier and Andrew L. Byrnes, Jr. February 1953. 
26p. diagrs., photos. (NACA RM L52L18) 



FLIGHT DETERMINATION OF THE STATIC LONGI- 
TUDINAL STABILITY BOUNDARIES OF THE BELL 
X-5 RESEARCH AIRPLANE WITH 59° SWEEPBACK. 
Thomas W. Finch and Joseph A. Walker. February 
1953. 51p. diagrs., photo., tab. 
(NACA RM L53A09b) 



LIFT AND DRAG CHARACTERISTICS OF THE 
BELL X-5 RESEARCH AIRPLANE AT 59° SWEEP- 
BACK FOR MACH NUMBERS FROM 0.60 TO 1.03, 
Donald R. Bellman. February 1953. 37p. diagrs., 
photos., tab. (NACA RM L53A09c) 



PRESSURE DISTRIBUTION AT MACH NUMBERS UP 
TO 0.90 ON A CAMBERED AND TWISTED WING 
HAVING 40° OF SWEEPBACK AND AN ASPECT 
RATIO OF 10, INCLUDING THE EFFECTS OF 
FENCES. Frederick W. Boltz and Harry H. 
Shibata. March 1953. 133p. diagrs., photos., tabs. 
(NACA RM A52K20) 



WIND-TUNNEL INVESTIGATION OF STALL CON- 
TROL BY SUCTION THROUGH A POROUS LEADING 
EDGE ON A 37° SWEPTBACK WING OF ASPECT 
RATIO 6 AT REYNOLDS NUMBERS FROM 2.50 xlO 6 
to B.10 x 10 6 , Robert R. Graham and William A. 
Jacques. March 1953. 67p. diagrs., photo., 2 tabs. 
(NACA RM L52L05) 



INVESTIGATIONS OF THE DAMPING IN ROLL OF 
SWEPT AND TAPERED WINGS AT SUPERSONIC 
SPEEDS. Russell W. McDearmon and Harry S. 
Heinke, Jr. March 1953. 35p. diagrs., photos., 
tab. (NACA RM L53A13) 

TESTS IN THE AMES 40- BY 80 -FOOT WIND TUN- 
NEL OF AN AIRPLANE CONFIGURATION WITH AN 
ASPECT RATIO 3 TRIANGULAR WING AND AN 
ALL-MOVABLE HORIZONTAL TAIL - LONGITU- 
DINAL AND LATERAL CHARACTERISTICS. David 
G. Koenig. April 1953. 61p. diagrs., photos., 
4 tabs. (NACA RM A52L15) 



THE EFFECT AT HIGH SUBSONIC SPEEDS OF A 
FLAP-TYPE AILERON ON THE CHORDWISE PRES- 
SURE DISTRIBUTION NEAR MIDSEMISPAN OF A 
TAPERED 35° SWEPTBACK WING OF ASPECT 
RATIO 4 HAVING NACA 65A006 AIRFOIL SECTION. 
Alexander D. Hammond and Barbara M. Keffer. 
May 1953. 89p. diagrs., tab. (NACA RM L53C23) 



THE LOW-SPEED LIFT AND DRAG CHARACTER- 
ISTICS OF A SERIES OF AIRPLANE MODELS 
HAVING TRIANGULAR OR MODIFIED TRIANGULAR 
WINGS. David Graham. June 1953. 49p. diagrs., 
photo., tabs. (NACA RM A53D14) 



TESTS IN THE AMES 40- BY 80-FOOT WIND TUN- 
NEL OF AN AIRPLANE CONFIGURATION WITH A 
VARIABLE -INCIDENCE TRIANGULAR WING AND 
AN ALL-MOVABLE HORIZONTAL TAIL. David G. 
Koenig, June 1953. 42p. diagrs., photo., tabs. 
(NACARM A53D21) 



LONGITUDINAL STABILITY AND WAKE-FLOW 
CHARACTERISTICS OF A TWISTED AND 
CAMBERED WING-FUSELAGE COMBINATION OF 
45° SWEEPBACK AND ASPECT RATIO 8 WITH A 
HORIZONTAL TAIL AND STALL-CONTROL DE- 
VICES AT A REYNOLDS NUMBER OF 4.0 x 10 6 
Gerald V. Foster. June 1953. 51p. diagrs., 
photos., tab. (NACA RM L53D08) 



29 



EFFECTS OF HORIZONTAL-TAIL HEIGHT AND A 
WING LEADING-EDGE MODIFICATION CON- 
SISTING OF A FULL-SPAN FLAP AND A PARTIAL- 
SPAN CHORD-EXTENSION ON THE AERODYNAMIC 
CHARACTERISTICS IN FITCH AT HIGH SUBSONIC 
SPEEDS OF A MODEL WITH A 45° SWEPTBACK 
WING. William D. Morrison, Jr. and William J. 
Alford, Jr. June 1953. 37p. diagrs., photo., tab. 
(NACA RM L53E06) 



WIND-TUNNEL INVESTIGATION OF THE EFFECTS 
OF GEOMETRIC DIHEDRAL ON THE AERODYNAM- 
IC CHARACTERISTICS IN PITCH AND SIDESLIP OF 
AN UNSWEPT- AND A 45° SWEPTBACK-WING- 
FUSELAGE COMBINATION AT HIGH SUBSONIC 
SPEEDS. Richard E. Kuhn and John W. Draper. 
July 1953. 41p, diagrs., photos. 
(NACA RM L53F09) 



THE EFFECTS OF LEADING-EDGE EXTENSIONS 
A TRAILING-EDGE EXTENSION, AND A FENCE ' 
ON THE STATIC LONGITUDINAL STABILITY OF A 
WING-FUSELAGE-TAIL COMBINATION HAVING 
A WING WITH 350 F SWEEPBACK AND AN AS- 
PECT RATIO OF 4.5. Ralph Selan and Angelo 
Bandettini. August 1953. 81p. diagrs,, photos. 
tabs, (NACA RM A53E12) 



THE EFFECTS OF FENCES ON THE HIGH-SPEED 
LONGITUDINAL STABILITY OF A SWEPT -WING 
AIRPLANE. Richards. Bray. August 1953. 37p. 
diagrs., photos., tabs. (NACA RM A53F23) 



A TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE LONGITUDINAL STABILITY AND CONTROL 
CHARACTERISTICS OF A 0.09-SCALE MODEL OF 
THE BELL X-5 RESEARCH AIRPLANE AND COM- 
PARISON WITH FLIGHT. Ralph P. Bielat and 
George S. Campbell. October 1953. 65p. diagrs. 
photo. (NACA RM L53H18) 



LOW-SPEED WIND-TUNNEL INVESTIGATION OF A 
JET CONTROL ON A 35° SWEPT WING. John G. 
Lowry and Thomas R. Turner. October 1953. 9p. 
diagrs. (NACA RM L53I09a) 



FREE-FLIGHT -TUNNEL INVESTIGATION OF THE 
LOW-SPEED STABILITY AND CONTROL CHARAC- 
TERISTICS OF A CANARD AIRPLANE MODEL. 
Joseph L. Johnson, Jr., and John W. Paulson. 
October 1953. 37p. diagrs., photo., 2 tabs. (NACA 
RM L53I11) 



SOME EFFECTS OF AEROELASTICITY AND 
SWEEPBACK ON THE ROLLING EFFECTIVENESS 
AND DRAG OF A 1/11-SCALE MODEL OF THE 
BELL X-5 AIRPLANE WING AT MACH NUMBERS 
FROM 0.6 TO 1.5, Roland D. English. November 
1953. 21p. diagrs., photos. (NACA RM L53Il8b) 



WIND-TUNNEL INVESTIGATION OF THE EFFECTS 
OF STEADY ROLLING ON THE AERODYNAMIC 
LOADING CHARACTERISTICS OF A 45° SWEPT- 
BACK WING AT HIGH SUBSONIC SPEEDS. James 
W. Wiggins and Richard E. Kuhn. November 1953. 
22p. diagrs., photos. (NACA RM L53J01a) 



( 1 ) AERODYNAMICS 



WIND-TUNNEL INVESTIGATION AT LOW SPEED 
OF THE EFFECT OF VARYING THE RATIO OF 
BODY DIAMETER TO WING SPAN FROM 0.1 TO 8 
ON THE AERODYNAMIC CHARACTERISTICS IN 
FITCH OF A 45° SWEPTBACK-WING-BODY 
COMBINATION. Harold S. Johnson. November 
1953. 32p. diagrs.. photo., tab. 
(NACA RM L53J09a) 

WIND-TUNNEL INVESTIGATION AT HIGH AND LOW 
SUBSONIC MACH NUMBERS OF TWO UNSWEPT 
WINGS HAVING NACA 2-006 AND NACA 65A006 
AIRFOIL SECTIONS. Stanley F. Racisz. 
December 1953. 40p. diagrs., photo., tab. 
(NACA RM L53J29) 

A STUDY OF THE PROBLEM OF DESIGNING AIR- 
PLANES WITH SATISFACTORY INHERENT DAMP- 
ING OF THE DUTCH ROLL OSCILLATION. John P. 
Campbell and Marion O. McKinney, Jr. 1954. ii 
18p. diagrs., tabs. (NACA Rept. 1199. Super- 
sedes TN 3035) 



WIND-TUNNEL INVESTIGATION AT LOW SPEED 
OF THE EFFECTS OF CHORDWISE WING FENCES 
AND HORIZONTAL-TAIL POSITION ON THE 
STATIC LONGITUDINAL STABILITY CHARACTER- 
ISTICS OF AN AIRPLANE MODEL WITH A 35° 
SWEPTBACK WING. M. J. Queljo, Byron M. 
Jaquet, and Walter D. Wolhart. 1954. 11, 29p. 
diagrs., photos., tab. (NACA Rept. 1203. Super- 
sedes RM L50K07; RM L51H17) 



A COMPARISON OF THE SPANWISE LOADING 
CALCULATED BY VARIOUS METHODS WITH EX- 
PERIMENTAL LOADINGS OBTAINED ON A 45° 
SWEPTBACK WING OF ASPECT RATIO 8.C2 AT A 
REYNOLDS NUMBER OF 4.0 x 10 6 . William C. 
Schneider. 1954. ii, lip. diagrs., tab. 
(NACA Kept. 1208. Supersedes RM L5iG30) 

STABILITY CHARACTERISTICS AT LOW SPEED OF 
A VARIABLE -SWEEP AIRPLANE MODEL HAVING 
A PARTIALLY CAMBERED WING WITH SEVERAL 
CHORD-EXTENSION CONFIGURATIONS. Robert E. 
Becht. February 1954. 37p. diagrs., photos. 
(NACA RM L53L14) 



THE EFFECTS OF HORIZONTAL-TAIL HEIGHT 
AND A PARTIAL-SPAN LEADING-EDGE EXTEN- 
SION ON THE STATIC LONGITUDINAL STABILITY 
OF A WING-FUSELAGE-TAIL COMBINATION 
HAVING A SWEPTBACK WING. Angelo Bandettini 
and Ralph Selan. March 1954. 54p. diagrs., 
photos., 2 tabs. (NACA RM A53J07) 

DISTRIBUTION OB LIFT AND PITCHING MOMENT 
BETWEEN WING AND FUSELAGE AND EFFECTS 
OF WING FLEXIBILITY AND DIVE BRAKE ON A 
1. 30-SCALE SEMISPAN MODEL OF THE BELL X-5 
AIRPLANE AT TRANSONIC SPEEDS AS DETER- 
MINED BY THE NACA WING-FLOW METHOD. 
Garland J. Morris and Norman S. Silsby. March 
1054. 4Cp. diagrs., photos., tab. 
(NACA RM L54A11) 



CHORDWISE PRESSURES AND SECTION FORCE 
AND MOMENT COEFFICIENTS AT HIGH SUBSONIC 
SPEEDS NEAR MIDSPAN OF A TAPERED 35° 
SWEPTBACK WING WITH A FLAP-TYPE CONTROL 
AND AN ATTACHED TAB. Alexander D. Hammond 
and Barbara M. Keffer. March 1954. 57p. diagrs 
35 tabs. (NACA RM L54A22) 



30 



(1) AERODYNAMICS 



HINGE-MOMENT, LIFT, AND PITCHING-MOMENT 
CHARACTERISTICS OF A FLAP-TYPE CONTROL 
SURFACE HAVING VARIOUS HINGE-LINE LOCA- 
TIONS ON A 4-PERCENT-THICK 60° DELTA WING. 
TRANSONIC -BUMP METHOD. Robert F. Thompson. 
March 1954. 73p. diagrs., photo. 
(NACA RM L54B08) 



EFFECTS OF OPERATING PROPELLERS ON THE 
WING-SURFACE PRESSURES OF A FOUR-ENGINE 
TRACTOR AIRPLANE CONFIGURATION HAVING A 
WING WITH 40° OF SWEEPBACK. Carl D. Kolbe 
and Frederick W. Boltz. April 1954. 133p. 
diagrs, , photo., 19 tabs. (NACA RM A53L29) 

EFFECTS OF SWEEP AND THICKNESS ON THE 
STATIC LONGITUDINAL AERODYNAMIC CHARAC- 
TERISTICS OF A SERIES OF THIN, LOW-ASPECT- 
RATIO, HIGHLY TAPERED WINGS AT TRANSONIC 
SPEEDS. TRANSONIC-BUMP METHOD. Albert G. 
Few, Jr., and Paul G. Fournier. April 1954. 107p. 
diagrs., photo., tab. (NACA RM L54B25) 

EFFECT AT TRANSONIC SPEEDS OF INBOARD 
SPOILERS ON THE STATIC LONGITUDINAL STA- 
BILITY CHARACTERISTICS OF A 45° SWEPTBACK 
WING-BODY COMBINATION HAVING A LEADING- 
EDGE CHORD-EXTENSION. James H. Henderson. 
June 1954. 24p. diagrs., photo. 
(NACA RM L54D13) 

STATIC LONGITUDINAL STABILITY CHARACTER- 
ISTICS OF A COMPOSITE-PLAN-FORM WING 
MODEL INCLUDING SOME COMPARISONS WITH A 
45° SWEPTBACK WING AT TRANSONIC SPEEDS. 
Walter D. Wolhart. August 1954. 36p. diagrs., 
photo., tabs. (NACA RM L54F24) 



EFFECT OF GROUND INTERFERENCE ON THE 
AERODYNAMIC AND FLOW CHARACTERISTICS OF 
A 42° SWEPTBACK WING AT REYNOLDS NUMBERS 
UP TO 6.8 x 10 6 . G. Chester Furlong and Thomas 
V. Bollech. 1955. ii, 60p. diagrs., photos., tab. 
(NACA Rept. 1218. Combination of RM L8G22; 
TN 2487) 



EFFECTS OF WING POSITION AND FUSELAGE 
SIZE ON THE LOW-SPEED STATIC AND ROLLING 
STABILITY CHARACTERISTICS OF A DELTA-WING 
MODEL. Alex Goodman and David F. Thomas, Jr. 
1955. ii, 31p. diagrs., photos., tabs. 
(NACA Rept. 1224. Supersedes TN 3063) 



AN INVESTIGATION OF THE MAXIMUM LIFT OF 
WINGS AT SUPERSONIC SPEEDS. James J. 
Gallagher and James N. Mueller. 1955. ii, 28p. 
diagrs., photos., tabs. (NACA Rept. 1227. Super- 
sedes RM L7J10) 



A FLIGHT EVALUATION OF THE LONGITUDINAL 
STABILITY CHARACTERISTICS ASSOCIATED WITH 
THE PITCH-UP OF A SWEPT -WING AIRPLANE IN 
MANEUVERING FLIGHT AT TRANSONIC SPEEDS. 
Seth B. Anderson and Richard S. Bray. 1955. ii, 
12p. diagrs., photo., tab. (NACA Rept. 1237. 
Supersedes RM A5 111 2) 



WING-LOAD MEASUREMENTS OF THE BELL X-5 
RESEARCH AIRPLANE AT A SWEEP ANGLE OF 
58.7°. Richard D. Banner, Robert D. Reed, and 
William L. Marcy. April 1955. 22p. diagrs., 
photo., tab. (NACA RM H55A11) 



FLIGHT DETERMINATION OF THE LONGITUDINAL 
STABILITY AND CONTROL CHARACTERISTICS OF 
THE BELL X-5 RESEARCH AIRPLANE AT 58.7° 
SWEEPBACK. Thomas W. Finch. May 1955. 30p. 
diagrs., photo., tab. (NACA RM H55C07) 

FLIGHT TESTS OF LEADING-EDGE AREA SUCTION 
ON A FIGHTER-TYPE AIRPLANE WITH A 35° 
SWEPTBACK WING. Richard S. Bray and Robert C. 
Innis. June 1955. 30p. diagrs., photos., tab. 
(NACA RM A55C07) 

EFFECTS OF SWEEP ON THE MAXIMUM -LIFT 
CHARACTERISTICS OF FOUR ASPECT-RATIO-4 
WINGS AT TRANSONIC SPEEDS. Thomas R. Turner. 
July 1955. 25p. diagrs. (NACA TN 3468. Formerly 
RM L50H11) 



SUMMARY OF RESULTS OF A WIND-TUNNEL 
INVESTIGATION OF NINE RELATED HORIZONTAL 
TAILS. Jules B. Dods, Jr. and Bruce E. Tinling. 
July 1955. 105p. diagrs., 2 tabs. (NACA TN 3497. 
Formerly RM A51G31a) 

CORRECTION OF ADDITIONAL SPAN LOADINGS 
COMPUTED BY THE WEISSINGER SEVEN-POINT 
METHOD FOR MODERATELY TAPERED WINGS 
OF HIGH ASPECT RATIO. John DeYoung and 
Walter H. Barling, Jr. July 1955. 31p. diagrs. 
(NACA TN 3500) 

EFFECTS OF SWEEP AND ANGLE OF ATTACK ON 
BOUNDARY-LAYER TRANSITION ON WINGS AT 
MACH NUMBER 4.04. Robert W. Dunning and 
Edward F. Ulmann. August 1955. 31p. diagrs., 
photos. (NACA TN 3473) 

THE EFFECTIVENESS OF WING VORTEX GENERA- 
TORS IN IMPROVING THE MANEUVERING CHARAC- 
TERISTICS OF A SWEPT-WING AIRPLANE AT 
TRANSONIC SPEEDS. Norman M. McFadden, 
George A. Rathert, Jr., and Richard S. Bray. 
September 1955. 43p. diagrs. , photos. , tab. 
(NACA TN 3523. Supersedes RM A51J18) 

CALCULATED SPANWISE LIFT DISTRIBUTIONS 
AND AERODYNAMIC INFLUENCE COEFFICIENTS 
FOR SWEPT WINGS IN SUBSONIC FLOW. 
Franklin W. Diederich and Martin Zlotnick. 
October 1955. 173p. diagrs., tabs. (NACA 
TN 3476) 

SUMMARY OF RESULTS OBTAINED BY 
TRANSONIC -BUMP METHOD ON EFFECTS OF 
PLAN FORM AND THICKNESS ON LIFT AND DRAG 
CHARACTERISTICS OF WINGS AT TRANSONIC 
SPEEDS. Edward C. Polhamus. November 1955. 
33p. diagrs., tab. (NACA TN 3469. Supersedes 
RM L51H30) 

EXPERIMENTAL INVESTIGATION AT LOW SPEED 
OF EFFECTS OF FUSELAGE CROSS SECTION ON 
STATIC LONGITUDINAL AND LATERAL STABILITY 
CHARACTERISTICS OF MODELS HAVING 0° AND 
45° SWEPTBACK SURFACES. William Letko and 
James L. Williams. December 1955. 45p. diagrs., 
tabs. (NACA TN 3551) 



THEORETICAL SPAN LOAD DISTRIBUTIONS AND 
ROLLING MOMENTS FOR SIDESLIPPING WINGS 
OF ARBITRARY PLAN FORM IN INCOMPRESSIBLE 
FLOW. M. J. Queijo. December 1955. 45p. 
diagrs. (NACA TN 3605) 



31 



(1) AERODYNAMICS 



PRELIMINARY STUDY OF SOME FACTORS WHICH 
AFFECT THE STALL-FLUTTER CHARACTER- 
ISTICS OF THIN WINGS. A. Gerald Rainey. March 
1956. 33p. diagrs., photo., tab. (NACA TN 3622. 
Supersedes RM L52D08) 

AN ANALYSIS OF ESTIMATED AND EXPERI- 
MENTAL TRANSONIC DOWNWASH CHARACTER- 
ISTICS AS AFFECTED BY PLAN FORM AND THICK- 
NESS FOR WING AND WING- FUSELAGE CONFIG- 
URATIONS. Joseph Well, George S. Campbell and 
Margaret S. Dlederich. April 1956. 92p. diagrs., 
photos., tabs. (NACA TN 3628. Supersedes 
RM L52I22) 

THEORETICAL PRESSURE DISTRIBUTIONS FOR 
SOME SLENDER WING-BODY COMBINATIONS AT 
ZERO LIFT. Paul F. Byrd. April 1956. 39p. 
diagrs. (NACA TN 3674. Supersedes RM A54J07) 



INVESTIGATION BY THE TRANSONIC -BUMP 
METHOD OF A 35° SWEPTBACK SEMISPAN 
MODEL EQUIPPED WITH A FLAP OPERATED BY 
A SERIES OF SERVOVANES LOCATED AHEAD OF 
AND GEARED TO THE FLAP. William H. Phillips 
and Robert F. Thompson. April 1956. 39p. diagrs., 
photo. (NACA TN 3689. Supersedes RM L51J10) 



WIND-TUNNEL INVESTIGATION OF THE EFFECT 
OF CLIPPING THE TIPS OF TRIANGULAR WINGS 
OF DIFFERENT THICKNESS, CAMBER, AND AS- 
PECT RATIO - TRANSONIC BUMP METHOD. 
Horace F. Emerson. June 1356. 183p. diagrs., 
photo., tabs. (NACA TN 3671. Supersedes 
RM A53L03) 



FLIGHT TESTS AT SUPERSONIC SPEEDS TO 
DETERMINE THE EFFECT OF TAPER ON THE 
ZERO-LIFT DRAG OF SWEPTBACK LOW-ASPECT- 
RATIO WINGS. Murray Pittel. June 1956. 20p. 
diagrs., photos. (NACA TN 3697. Supersedes 
RM L50F30a) 



PRELIMINARY WIND-TUNNEL TESTS OF TRIAN- 
GULAR AND RECTANGULAR WINGS IN STEADY 
ROLL AT MACH NUMBERS OF 1.62 AND 1.92. 
Clinton E. Brown and Harry S. Heinke, Jr. 
June 1956. 36p. diagrs., tabs. 
(NACA TN 3740. Supersedes RM L8L30) 



(1.2.2.2.4) 

Taper and Twist 



FREE-FLIGHT INVESTIGATION OF CONTROL EF- 
FECTIVENESS OF FULL-SPAN, 0.2-CHORD PLAIN 
AILERONS AT HIGH SUBSONIC, TRANSONIC, AND 
SUPERSONIC SPEEDS TO DETERMINE SOME EF- 
FECTS OF WING SWEEPBACK, TAPER, ASPECT 
RATIO, AND SECTION-THICKNESS RATIO. Carl A. 
Sandahl. August 13, 1947. 16p. diagrs., photos., 
tab. (NACA RM L7F30) 



FREE- FLIGHT INVESTIGATION OF THE ROLLING 
EFFECTIVENESS AT HIGH SUBSONIC, TRANSONIC, 
AND SUPERSONIC SPEEDS OF LEADING-EDGE 
AND TRAILING-EDGE AILERONS IN CONJUNCTION 
WITH TAPERED AND UNTAPERED PLAN FORMS. 
H. Kurt Strass. July 23, 1948. 19p. diagrs., 
photos. (NACA RM L8E10) 



CHARACTERISTICS THROUGHOUT THE SUBSONIC 
SPEED RANGE OF A PLANE WING AND OF A 
CAMBERED AND TWISTED WING, BOTH HAVING 
45° OF SWEEPBACK. Ben H. Johnson, Jr., and 
Harry H. Shibata. July 1951. 122p, diagrs., 
photos. (NACA RM A51D27) 



A PRELIMINARY WIND-TUNNEL INVESTIGATION 
OF FLUTTER CHARACTERISTICS OF DELTA 
WINGS. Robert W. Herr. April 1952. 35p. 
diagrs., tabs. (NACA RM L52B14a) 



AN INVESTIGATION THROUGHOUT THE SUBSONIC 
SPEED RANGE OF A FULL-SPAN AND A SEMI- 
SPAN MODEL OF A PLANE WING AND OF A 
CAMBERED AND TWISTED WING, ALL HAVING 
45° OF SWEEPBACK. Harry H. Shibata, Angelo 
Bandettini, and Joseph Cleary. June 1952. 65p. 
diagrs., photos. (NACA RM A52D01) 



TRANSONIC FLIGHT TESTS TO DETERMINE THE 
EFFECT OF THICKNESS RATIO AND PLAN-FORM 
MODIFICATION ON THE ZERO-LIFT DRAG OF A 
45° SWEPTBACK WING. William B. Pepper, Jr., 
and Sherwood Hoffman. August 1952. 24p. diagrs., 
photos., tabs. (NACA RM L52F02a) 



THE LONGITUDINAL CHARACTERISTICS AT MACH 
NUMBERS UP TO 0.92 OF A CAMBERED AND 
TWISTED WING HAVING 40° OF SWEEPBACK AND 
AN ASPECT RATIO OF 10. George G. Edwards, 
Bruce E. Tinling, and Arthur C. Ackerman. 
September 1952. 71p. diagrs., photos., tab. 
(NACA RM A52F18) 



EFFECTS OF TWIST AND CAMBER, FENCES, AND 
HORIZONTAL -TAIL HEIGHT ON THE LOW-SPEED 
LONGITUDINAL STABILITY CHARACTERISTICS OF 
A WING- FUSELAGE COMBINATION WITH A 45° 
SWEPTBACK WING OF ASPECT RATIO 8 AT A 
REYNOLDS NUMBER OF 4.0 x 10^. Gerald V. 
Foster. December 1952. 30p. diagrs., photo. 
(NACA RM L52J03) 



PRESSURE DISTRIBUTION AT MACH NUMBERS UP 
TO 0.90 ON A CAMBERED AND TWISTED WING 
HAVING 40° OF SWEEPBACK AND AN ASPECT 
RATIO OF 10, INCLUDING THE EFFECTS OF 
FENCES. Frederick W. Boltz and Harry H. 
Shibata. March 1953. 133p. diagrs., photos., tabs. 
(NACA RM A52K20) 



EXPERIMENTAL INVESTIGATION OF THE EF- 
FECTS OF PLAN-FORM TAPER ON THE AERO- 
DYNAMIC CHARACTERISTICS OF SYMMETRICAL 
UNSWEPT WINGS OF VARYING ASPECT RATIO. 
Edwin C. Allen. May 1953. 53p. diagrs., photos,, 
tab. (NACA RM A53C19) 



LONGITUDINAL STABILITY AND WAKE-FLOW 
CHARACTERISTICS OF A TWISTED AND 
CAMBERED WING-FUSELAGE COMBINATION OF 
45° SWEEPBACK AND ASPECT RATIO 8 WITH A 
HORIZONTAL TAIL AND STALL-CONTROL DE- 
VICES AT A REYNOLDS NUMBER OF 4.0 x 10 6 . 
Gerald V. Foster. June 1953. 51p. diagrs., 
photos., tab. (NACA RM L53D08) 



32 



( 1 ) AERODYNAMICS 



WIND-TUNNEL INVESTIGATION OF THE AERODY- 
NAMIC CHARACTERISTICS IN PITCH OF WING- 
FUSELAGE COMBINATIONS AT HIGH SUBSONIC 
SPEEDS. TAPER- RATIO SERIES. Thomas J. 
King, Jr. and Thomas B. Pasteur, Jr. Juno 1953. 
37p. diagrs.. photos., tab. (NACA RM L53E20) 



DETERMINATION OF MEAN CAMBER SURFACES 
FOR WINGS HAVING UNIFORM CHORDWISE LOAD- 
ING AND ARBITRARY SPANWISE LOADING IN 
SUBSONIC FLOW. S. Katzoff, M. Frances Faison 
and Hugh C. DuBose. 1954. ii, 17p. diagrs., tab. 
(NACA Rept. 1176. Formerly TN 2908) 



THE TRANSONIC CHARACTERISTICS OF UNSWEPT 
WINGS HAVING ASPECT RATIOS OF 4, SPANWISE 
VARIATIONS IN THICKNESS RATIO, AND VARIA- 
TIONS IN PLAN-FORM TAPER - TRANSONIC- 
BUMP TECHNIQUE. Warren H. Nelson. March 
1954. 29p. diagrs., photo. (NACA RM A53L17) 



CALCULATED SPANWISE LIFT DISTRIBUTIONS, 
INFLUENCE FUNCTIONS, AND INFLUENCE COEF- 
FICIENTS FOR UNSWEPT WINGS IN SUBSONIC 
FLOW. Franklin W. Diederich and Martin Zlotnick. 
1955. ii, 69p. diagrs., tabs. (NACA Rept. 1228. 
Supersedes TN 3014) 



CALCULATED SPANWISE LIFT DISTRIBUTIONS 
AND AERODYNAMIC INFLUENCE COEFFICIENTS 
FOR SWEPT WINGS IN SUBSONIC FLOW. 
Franklin W. Diederich and Martin Zlotnick. 
October 1955. 173p. diagrs., tabs. (NACA 
TN 3476) 



THE TRANSONIC CHARACTERISTICS OF 36 SYM- 
METRICAL WINGS OF VARYING TAPER, ASPECT 
RATIO, AND THICKNESS AS DETERMINED BY THE 
TRANSONIC-BUMP TECHNIQUE. Warren H. 
Nelson, Edwin C. Allen, and Walter J. Krumm. 
December 1955. 131p. diagrs., photo. 
(NACA TN 3529. Supersedes RM A53I29) 



THEORETICAL SPAN LOAD DISTRIBUTIONS AND 
ROLLING MOMENTS FOR SIDESLIPPING WINGS 
OF ARBITRARY PLAN FORM IN INCOMPRESSIBLE 
FLOW. M. J. Queijo. December 1955. 45p. 
diagrs. (NACA TN 3605) 



WIND-TUNNEL INVESTIGATION OF THE EFFECT 
OF CLIPPING THE TIPS OF TRIANGULAR WINGS 
OF DIFFERENT THICKNESS, CAMBER, AND AS- 
PECT RATIO - TRANSONIC BUMP METHOD. 
Horace F. Emerson. June 1956. 183p. diagrs., 
photo., tabs. (NACA TN3671. Supersedes 
RM A53L03) 



FLIGHT TESTS AT SUPERSONIC SPEEDS TO 
DETERMINE THE EFFECT OF TAPER ON THE 
ZERO-LIFT DRAG OF SWEPTBACK LOW-ASPECT- 
RATIO WINGS. Murray Pittel. June 1956. 20p. 
diagrs., photos. (NACA TN 3697. Supersedes 
RM L50F30a) 



(1.2.2.2.5) 
Inlets and Exits 

INVESTIGATION OF THE EFFECTS OF WING AND 
TAIL MODIFICATIONS ON THE LOW-SPEED STA- 
BILITY CHARACTERISTICS OF A MODEL HAVING 
A THIN 40° SWEPT WING OF ASPECT RATIO 3.5. 
Joseph Weil, William C. Sleeman, Jr., and Andrew 
L. Byrnes, Jr. April 1953. 95p. diagrs., photos., 
tab. (NACA RM L53C09) 

(1.2.2.2.6) 
Surface Conditions 

CHARACTERISTICS THROUGHOUT THE SUBSONIC 
SPEED RANGE OF A PLANE WING AND OF A 
CAMBERED AND TWISTED WING, BOTH HAVING 
45° OF SWEEPBACK. Ben H. Johnson, Jr., and 
Harry H. Shibata. July 1951. 122p. diagrs., 
photos. (NACA RM A51D27) 



TRANSONIC -WING INVESTIGATION IN THE 
LANGLEY 8-FOOT HIGH-SPEED TUNNEL AT HIGH 
SUBSONIC MACH NUMBERS AND AT A MACH NUM- 
BER OF 1.2. ANALYSIS OF PRESSURE DISTRIBU- 
TION OF WING-FUSELAGE CONFIGURATION HAV- 
ING A WING OF 45° SWEEPBACK, ASPECT RATIO 
4, TAPER RATIO 0.6, AND NACA 65A006 AIRFOIL 
SECTION. Donald L. Loving and Bruce B. 
Estabrooks. September 1951. 132p, diagrs., photos, 
(NACA RM L51F07) 



AN INVESTIGATION THROUGHOUT THE SUBSONIC 
SPEED RANGE OF A FULL-SPAN AND A SEMI- 
SPAN MODEL OF A PLANE WING AND OF A 
CAMBERED AND TWISTED WING, ALL HAVING 
45° OF SWEEPBACK. Harry H. Shibata, Angelo 
Bandettini, and Joseph Cleary, June 1952. 65p. 
diagrs., photos. (NACA RM A52D01) 



WIND-TUNNEL INVESTIGATION AT HIGH AND LOW 
SUBSONIC MACH NUMBERS OF TWO UNSWEPT 
WINGS HAVING NACA 2-006 AND NACA 65A006 
AIRFOIL SECTIONS. Stanley F. Racisz. 
December 1953. 40p. diagrs., photo., tab. 
(NACA RM L53J29) 



THE EFFECTIVENESS OF WING VORTEX GENERA- 
TORS IN IMPROVING THE MANEUVERING CHARAC- 
TERISTICS OF A SWEPT-WING AIRPLANE AT 
TRANSONIC SPEEDS. Norman M. McFadden, 
George A. Rathert, Jr., and Richard S. Bray. 
September 1955. 43p. diagrs. , photos. , tab. 
(NACA TN 3523. Supersedes RM A51J18) 



(1. 2. 2.2. 7) 
Dihedral 

A COMPARISON OF THE EXPERIMENTAL AND 
THEORETICAL LOADING OVER TRIANGULAR 
WINGS IN SIDESLIP AT SUPERSONIC SPEEDS. 
John W. Boyd. May 18, 1951. 58p. diagrs., photo., 
tabs. (NACA RM A51C13) 

AN APPROXIMATION TO THE EFFECT OF GEO- 
METRIC DIHEDRAL ON THE ROLLING MOMENT 
DUE TO SIDESLIP FOR WINGS AT TRANSONIC AND 
SUPERSONIC SPEEDS. Paul E. Purser. April 
1952. lOp. diagrs. (NACA RM L52B01) 



33 



(1) AERODYNAMICS 



WIND-TUNNEL INVESTIGATION OF THE EFFECTS 
OF GEOMETRIC DIHEDRAL ON THE AERODYNAM- 
IC CHARACTERISTICS IN PITCH AND SIDESLIP OF 
AN UNSWEPT- AND A 45° SWEPTBACK-WING- 
FUSELAGE COMBINATION AT HIGH SUBSONIC 
SPEEDS. Richard E. Kuhn and John W. Draper. 
July 1953. 41p. diagrs., photos. 
(NACA RML53F09) 



A STUDY OF THE PROBLEM OF DESIGNING AIR- 
PLANES WITH SATISFACTORY INHERENT DAMP- 
ING OF THE DUTCH ROLL OSCILLATION. John P. 
Campbell and Marion O. McKinney, Jr. 1954. ii, 
18p. diagrs., tabs. (NACA Rept. 1199. Super- 
sedes TN 3035) 



LOW-SPEED STATIC LATERAL AND ROLLING 
STABILITY CHARACTERISTICS OF A SERIES OF 
CONFIGURATIONS COMPOSED OF INTERSECTING 
TRIANGULAR PLAN-FORM SURFACES. David F. 
Thomas, Jr. October 1955. 29p. diagrs., photos. 
(NACA TN 3532) 



(1.2. 2. 3) 
HIGH-LIFT DEVICES 



FREE-FLIGHT INVESTIGATION OF THE ROLLING 
EFFECTIVENESS AT HIGH SUBSONIC, TRANSONIC, 
AND SUPERSONIC SPEEDS OF LEADING-EDGE 
AND TRAILING-EDGE AILERONS IN CONJUNCTION 
WITH TAPERED AND UNTAPERED PLAN FORMS. 
H. Kurt Strass. July 23, 1948. 19p. diagrs., 
photos. (NACA RM L8E10) 



EFFECTS OF HORIZONTAL-TAIL HEIGHT AND A 
WING LEADING-EDGE MODIFICATION CON- 
SISTING OF A FULL-SPAN FLAP AND A PARTIAL- 
SPAN CHORD-EXTENSION ON THE AERODYNAMIC 
CHARACTERISTICS IN PITCH AT HIGH SUBSONIC 
SPEEDS OF A MODEL WITH A 45° SWEPTBACK 
WING. William D. Morrison, Jr. and William J. 
Alford, Jr. June 1953. 37p. diagrs., photo., tab. 
(NACA RM L53E06) 



EFFECTS OF HIGH-LIFT DEVICES AND 
HORIZONTAL-TAIL LOCATION ON THE LOW- 
SPEED CHARACTERISTICS OF A LARGE-SCALE 
45° SWEPT-WING AIRPLANE CONFIGURATION. 
Ralph L. Maki and Ursel R. Embry. August 1954. 
46p. diagrs., photo., tabs. (NACA RM A54E10) 



A LIMITED FLIGHT INVESTIGATION OF THE EF- 
FECT OF THREE VORTEX-GENERATOR CONFIGU- 
RATIONS ON THE EFFECTIVENESS OF A PLAIN 
FLAP ON AN UNSWEPT WING. Garland J. Morris 

and Lindsay J(ohn) Lina. September 1955. 20p. 
diagrs. , photos. , tabs. (NACA TN 3536) 



INVESTIGATION OF THE EFFECTS OF GROUND 
PROXIMITY AND PROPELLER POSITION ON THE 
EFFECTIVENESS OF A WING WITH LARGE-CHORD 
SLOTTED FLAPS IN REDIRECTING PROPELLER 
SLIPSTREAMS DOWNWARD FOR VERTICAL TAKE- 
OFF. Richard E. Kuhn. March 1956. 38p, 
diagrs., photos., tab. (NACA TN 3629) 



INVESTIGATION AT ZERO FORWARD SPEED OF A 
LEADING-EDGE SLAT AS A LONGITUDINAL CON- 
TROL DEVICE FOR VERTICALLY RISING AIR- 
PLANES THAT UTILIZE THE REDIRECTED- 
SLIPSTREAM PRINCIPLE. Richard E. Kuhn. 
May 1956. 33p. diagrs., photos. (NACA TN 3692) 



PRELIMINARY INVESTIGATION OF THE EFFEC- 
TIVENESS OF A SLIDING FLAP IN DEFLECTING A 
PROPELLER SLIPSTREAM DOWNWARD FOR 
VERTICAL TAKE-OFF. Richard E. Kuhn and 
Kenneth P. Spreemann. May 1956. 25p. diagrs., 
photo. (NACA TN 3693) 



(1. 2. 2. 3. 1) 

Trailing-Edge Flaps 



LONGITUDINAL STABILITY CHARACTERISTICS OF 
A 42° SWEPTBACK WING AND TAIL COMBINATION 
AT A REYNOLDS NUMBER OF 6.8 x 10 6 . Stanley H. 
Spooner and Albert P. Martina. July 22, 1948. 
44p. diagrs., photos., 2 tabs. (NACA RM L8E12) 



LONGITUDINAL -STABILITY INVESTIGATION OF 
HIGH-LIFT AND STALL-CONTROL DEVICES ON A 
52° SWEPTBACK WING WITH AND WITHOUT FUSE- 
LAGE AND HORIZONTAL TAIL AT A REYNOLDS 
NUMBER OF 6.8 x 10 6 . Gerald V. Foster and 
James E. Fitzpatrick. December 20, 1948. 41p. 
diagrs., photos., tabs. (NACA RM L8I08) 



HINGE-MOMENT MEASUREMENTS OF A WING 
WITH LEADING-EDGE AND TRAILING-EDGE 
FLAPS AT A MACH NUMBER OF 1. 93. William B. 
Boatright and Robert W. Rainey. January 14, 1949. 
12p. diagrs., tab. (NACA RM L8K12a) 



INVESTIGATION AT A MACH NUMBER OF 1.9 AND 
A REYNOLDS NUMBER OF 2.2 x 10 6 OF SEVERAL 
FLAP-TYPE LATERAL-CONTROL DEVICES ON A 
WING HAVING 42.7° SWEEPBACK OF THE LEAD- 
ING EDGE. KennithL. Goin. March 11, 1949. 
28p. diagrs., photos., tabs. (NACA RM L9A 18a) 



EFFECTS OF HIGH-LIFT AND STALL-CONTROL 
DEVICES, FUSELAGE, AND HORIZONTAL TAIL ON 
A WING SWEPT BACK 42° AT THE LEADING EDGE 
AND HAVING SYMMETRICAL CIRCULAR-ARC AIR- 
FOIL SECTIONS AT A REYNOLDS NUMBER OF 
6.9 x 10 6 . Robert L. Woods and Stanley H. 
Spooner. April 20, 1949, 42p. diagrs., photos., 
tabs. (NACA RM L9B11) 



A STUDY OF SEVERAL FACTORS AFFECTING THE 
STABILITY CONTRIBUTED BY A HORIZONTAL 
TAIL AT VARIOUS VERTICAL POSITIONS ON A 
SWEPTBACK-WING AIRPLANE MODEL. Gerald V. 
Foster and Roland F. Griner. October 28, 1949. 
28p. diagrs., tab. (NACA RM L9H19) 



EFFECTS OF VARYING THE SIZE AND LOCATION 
OF TRAILING-EDGE FLAP-TYPE CONTROLS ON 
THE AERODYNAMIC CHARACTERISTICS OF AN UN- 
SWEPT WING AT A MACH NUMBER OF 1.9. Meade 
H. Mitchell, Jr. August 16, 1950. 33p. diagrs., 
photo., tab. (NACA RM L50F08) 



34 



( 1 ) AERODYNAMICS 



LOW-SPEED LONGITUDINAL AND WAKE AIR- 
FLOW CHARACTERISTICS AT A REYNOLDS NUM- 
BER OF 6.0 x 10 6 OF A 52° SWEPTBACK WING 
EQUIPPED WITH VARIOUS SPANS OF LEADING- 
EDGE AND TRAILING-EDGE FLAPS, A FUSELAGE, 
AND A HORIZONTAL TAIL AT VARIOUS VERTICAL 
POSITIONS. Roland F. Griner and Gerald V. Foster. 
February 28, 1951. 66p. diagrs., photo., 3 tabs. 
(NACA RM L50K29) 



TESTS IN THE AMES 40- BY 80-FOOT WIND TUN- 
NEL OF AN AIRPLANE CONFIGURATION WITH AN 
ASPECT RATIO 2 TRIANGULAR WING AND AN 
ALL-MOVABLE HORIZONTAL TAIL- 
LONGITUDINAL CHARACTERISTICS. David Graham 
and David G. Koenig. April 23, 1951. 35p. diagrs., 
photo., 3 tabs. (NACA RM A51B2U 



LOW-SPEED LONGITUDINAL AND WAKE AIR- 
FLOW CHARACTERISTICS AT A REYNOLDS NUM- 
BER OF 5.5 x 10 6 OF A CIRCULAR-ARC 52° 
SWEPTBACK WING WITH A FUSELAGE AND A 
HORIZONTAL TAIL AT VARIOUS VERTICAL POSI- 
TIONS. Gerald V. Foster and Roland F. Griner. 
June 19, 1951. 44p. diagrs., tabs. 
(NACA RM L51C30) 



EFFECT OF VERTICAL LOCATION OF A HORIZON- 
TAL TAIL ON THE STATIC LONGITUDINAL STA- 
BILITY CHARACTERISTICS OF A 45° SWEPTBACK- 
WING - FUSELAGE COMBINATION OF ASPECT 
RATIO 8 AT A REYNOLDS NUMBER OF 4.0 x 10 6 . 
Relno J. Salmi and William A. Jacques. January 
1952. 42p. diagrs., photos. (NACA RM L51J08) 



TESTS IN THE AMES 40- BY 80-FOOT WIND TUN- 
NEL OF AN AIRPLANE CONFIGURATION WITH AN 
ASPECT RATIO 2 TRIANGULAR WING AND AN 
ALL-MOVABLE HORIZONTAL TAIL - LATERAL 
CHARACTERISTICS. David Graham and David G. 
Koenig. February 1952. 38p. diagrs., 2 tabs. 
(NACA RM A51L03) 



LOW-SPEED LATERAL-CONTROL CHARACTER- 
ISTICS OF AN UNSWEPT WING WITH HEXAGONAL 
AIRFOIL SECTIONS AND ASPECT RATIO 2.5 
EQUIPPED WITH SPOILERS AND WITH SHARP- 
AND THICKENED-TRAILING-EDGE FLAP-TYPE 
AILERONS AT A REYNOLDS NUMBER OF 7.6 x 10 6 . 
James E. Fitzpatrick and Robert L. Woods. April 
1952. 58p. photos., diagrs., tab. 
(NACA RM L52B15) 



INVESTIGATION OF THE LOW-SPEED AERO- 
DYNAMIC CHARACTERISTICS OF A VARIABLE - 
SWEEP AIRPLANE MODEL WITH A WING HAVING 
PARTIAL-SPAN CAMBERED- LEADING-EDGE 
MODIFICATIONS. Robert E. Becht and Andrew L. 
Byrnes, Jr. September 1952. 47p. diagrs., photos. 
(NACA RM L52G08a) 



TESTS IN THE AMES 40- BY 80-FOOT WIND TUN- 
NEL OF AN AIRPLANE MODEL WITH AN ASPECT 
RATIO 4 TRIANGULAR WING AND AN ALL- 
MOVABLE HORIZONTAL TAIL - HIGH-LIFT DE- 
VICES AND LATERAL CONTROLS. Ralph W. 
Franks. February 1953. 45p. diagrs., photo., 2 
tabs. (NACA RM A52K13) 



TESTS IN THE AMES 40- BY 80-FOOT WIND TUN- 
NEL OF TWO AIRPLANE MODELS HAVING AS- 
PECT RATIO 2 TRAPEZOIDAL WINGS OF TAPER 
RATIOS 0.33 AND 0.20. Ralph W. Franks. 
February 1953. 56p. diagrs., photos., 3 tabs. 
(NACA RM A52L16) 



THE EFFECTS OF FUSELAGE SIZE ON THE LOW- 
SPEED LONGITUDINAL AERODYNAMIC CHARAC- 
TERISTICS OF A THIN 60° DELTA WING WITH 
AND WITHOUT. A DOUBLE SLOTTED FLAP. John 
M. Riebe. February 1953. 24p. diagrs., photo., 
tab. (NACA RM L52L29a) 

LOW-SPEED LONGITUDINAL CHARACTERISTICS 
OF AN UNSWEPT HEXAGONAL WING WITH AND 
WITHOUT A FUSELAGE AND A HORIZONTAL TAIL 
LOCATED AT VARIOUS POSITIONS AT REYNOLDS 
NUMBERS FROM 2.8 x 10 6 TO 7.6 x 10 6 . Gerald V. 
Foster. Ernst F. Mollenberg, and Robert L. Woods. 
February 26, 1953. 63p. diagrs., photos., 3 tabs. 
(NACA RM L52Lllb) 

WIND-TUNNEL INVESTIGATION OF STALL CON- 
TROL BY SUCTION THROUGH A POROUS LEADING 
EDGE ON A 37° SWEPTBACK WING OF ASPECT 
RATIO 6 AT REYNOLDS NUMBERS FROM 2.50xl0 6 
to 8.10 x 10 6 . Robert R. Graham and William A. 
Jacques. March 1953. 67p. diagrs., photo., 2 tabs. 
(NACA RM L52L05) 



TESTS IN THE AMES 40- BY 80-FOOT WIND TUN- 
NEL OF AN AIRPLANE CONFIGURATION WITH AN 
ASPECT RATIO 3 TRIANGULAR WING AND AN 
ALL-MOVABLE HORIZONTAL TAIL - LONGITU- 
DINAL AND LATERAL CHARACTERISTICS. David 
G. Koenig. April 1953. 61p. diagrs., photos., 
4 tabs. (NACA RM A52L15) 

THE EFFECTS OF NACELLES AND OF EXTENDED 
SPLIT FLAPS ON THE LONGITUDINAL CHARAC- 
TERISTICS OF A WING-FUSELAGE-TAIL COMBI- 
NATION HAVING A WING WITH 40° OF SWEEP- 
BACK AND AN ASPECT RATIO OF 10. Bruce E, 
Tinling and Armando E. Lopez. June 1953. 47p. 
diagrs., tab. (NACA RM A53D06) 

THE LOW -SPEED LIFT AND DRAG CHARACTER- 
ISTICS OF A SERIES OF AIRPLANE MODELS 
HAVING TRIANGULAR OR MODIFIED TRIANGULAR 
WINGS. David Graham. June 1953. 49p. diagrs., 
photo., tabs. (NACA RM A53D14) 



TESTS IN THE AMES 40- BY 80-FOOT WIND TUN- 
NEL OF AN AIRPLANE CONFIGURATION WITH A 
VARIABLE-INCIDENCE TRIANGULAR WING AND 
AN ALL-MOVABLE HORIZONTAL TAIL. David G. 
Koenig. June 1953. 42p. diagrs., photo., tabs. 
(NACARM A53D21) 



LONGITUDINAL STABILITY AND WAKE-FLOW 
CHARACTERISTICS OF A TWISTED AND 
CAMBERED WING-FUSELAGE COMBINATION OF 
45° SWEEPBACK AND ASPECT RATIO 8 WITH A 
HORIZONTAL TAIL AND STALL-CONTROL DE- 
VICES AT A REYNOLDS NUMBER OF 4.0 x 10 6 . 
Gerald V. Foster. June 1953. 51p. diagrs., 
photos., tab. (NACA RM L53D08) 



THE LATERAL CONTROL CHARACTERISTICS OF 
CONSTANT-PERCENT-CHORD TRAILING-EDGE 
ELEVONS ON A POINTED WING OF ASPECT RATIO 
2 AT MACH NUMBERS UP TO 0.95. Verlin D. Reed 
and Donald W. Smith. August 1953. 105p. diagrs., 
photo., tabs. (NACA RM A53F03) 



35 



(1) AERODYNAMICS 



THE RESULTS OF WIND-TUNNEL TESTS AT LOW 
SPEEDS OF A FOUR-ENGINE PROPELLER-DRIVEN 
AIRPLANE CONFIGURATION HAVING A WING WITH 
40° OF SWEEPBACK AND AN ASPECT RATIO OF 
10. George G. Edwards, Donald A. Buell, and 
Jerald K. Dickson. December 1953. 121p. diagrs., 
photo., tabs. (NACA RM A53I28) 



WIND-TUNNEL INVESTIGATION AT HIGH AND LOW 
SUBSONIC MACH NUMBERS OF TWO UNSWEPT 
WINGS HAVING NACA 2-006 AND NACA 65A006 
AIRFOIL SECTIONS. Stanley F. Racisz. 
December 1953. 40p. diagrs., photo., tab. 
(NACA RM L53J29) 



WIND-TUNNEL INVESTIGATION AT LOW SPEED 
OF THE EFFECTS OF CHORDWISE WING FENCES 
AND HORIZONTAL-TAIL POSITION ON THE 
STATIC LONGITUDINAL STABILITY CHARACTER- 
ISTICS OF AN AIRPLANE MODEL WITH A 35<> 
SWEPTBACK WING. M. J. Queijo, Byron M. 
Jaquet, and Walter D. Wolhart. 1954. 11, 29p. 
diagrs., photos., tab. (NACA Rept. 1203. Super- 
sedes RM L50K07; RM L51H17) 



STABILITY CHARACTERISTICS AT LOW SPEED OF 
A VARIABLE-SWEEP AIRPLANE MODEL HAVING 
A PARTIALLY CAMBERED WING WITH SEVERAL 
CHORD-EXTENSION CONFIGURATIONS. Robert E. 
Becht. February 1954. 37p. diaers.. photos. 
(NACA RM L53L14) 



HINGE-MOMENT, LIFT, AND PITCHING-MOMENT 
CHARACTERISTICS OF A FLAP-TYPE CONTROL 
SURFACE HAVING VARIOUS HINGE-LINE LOCA- 
TIONS ON A 4-PERCENT-THICK 60° DELTA WING. 
TRANSONIC- BUMP METHOD. Robert F. Thompson. 
March 1954. 73p. diagrs., photo. 
(NACA RM L54B08) 



EFFECTS OF OPERATING PROPELLERS ON THE 
WING-SURFACE PRESSURES OF A FOUR-ENGINE 
TRACTOR AIRPLANE CONFIGURATION HAVING A 
WING WITH 40° OF SWEEPBACK. Car) D. Kolbe 
and Frederick W. Boltz. April 1954. 133p. 
diagrs., photo., 19 tabs. (NACA RM A53L29) 



EFFECTS OF HIGH-LIFT DEVICES AND 
HORIZONTAL-TAIL LOCATION ON THE LOW- 
SPEED CHARACTERISTICS OF A LARGE-SCALE 
45° SWEPT-WING AIRPLANE CONFIGURATION. 
Ralph L. Maki and Ursel R. Embry. August 1954. 
46p. diagrs., photo., tabs. (NACA RM A54E10) 



STATIC LONGITUDINAL STABILITY CHARACTER- 
ISTICS OF A COMPOSITE-PLAN-FORM WING 
MODEL INCLUDING SOME COMPARISONS WITH A 
45° SWEPTBACK WING AT TRANSONIC SPEEDS. 
Walter D. Wolhart. August 1954. 36p. diagrs., 
photo., tabs. (NACA RM L54F24) 



ANALYSIS OF WIND-TUNNEL TESTS AT LOW 
SPEEDS OF A FOUR-ENGINE PROPELLER- 
DRIVEN AIRPLANE CONFIGURATION HAVING A 
WING WITH 40° OF SWEEPBACK. George G. 
Edwards and Donald A. Buell. October 1954. 137p, 
diagrs., photos.. 2 tabs. (NACA RM A54F14) 



EFFECT OF GROUND INTERFERENCE ON THE 
AERODYNAMIC AND FLOW CHARACTERISTICS OF 
A 420 SWEPTBACK WING AT REYNOLDS NUMBERS 
UP TO 6.8 x 10 6 . G. Chester Furlong and Thomas 
V. Bollech. 1955. ii, 60p. diagrs., photos., tab. 
(NACA Rept. 1218. Combination of RM L8G22: 
TN 2487) 



THEORETICAL ANALYSES TO DETERMINE 
UNBALANCED TRAILING-EDGE CONTROLS 
HAVING MINIMUM HINGE MOMENTS DUE TO 
DEFLECTION AT SUPERSONIC SPEEDS. Kennith L. 
Goin. August 1955.52p. diagrs., tab. (NACA TN 3471. 
Formerly RM L51F19) 



A LIMITED FLIGHT INVESTIGATION OF THE EF- 
FECT OF THREE VORTEX-GENERATOR CONFIGU- 
RATIONS ON THE EFFECTIVENESS OF A PLAIN 
FLAP ON AN UNSWEPT WING. Garland J. Morris 
and Lindsay J(ohn) Lina. September 1955. 20p. 
diagrs. , photos. , tabs. (NACA TN 3536) 



THEORETICAL ANALYSIS OF LINKED LEADING- 
EDGE AND TRAILING-EDGE FLAP-TYPE CON- 
TROLS AT SUPERSONIC SPEEDS. E. Carson 
Yates, Jr. March 1956. 40p. diagrs.. tab 
(NACA TN 3617) 



A WIND-TUNNEL INVESTIGATION OF A 0.4 -SCALE 
MODEL OF AN ASSAULT-TRANSPORT AIRPLANE 



\U1TU DAHXTTi; 



.RY-T.AVFP rifiXTTiT^/^T „ . 



Marvin P. Fink, Bennie W. Cocke, and Stanley 
Lipson. May 1956. 63p. diagrs., photos. 
(NACA RM L55G26a) 



(1. 2.2. 3.2) 
Slots and Slats 

HIGH-SPEED STABIUTY AND CONTROL CHARAC- 
TERISTICS OF A FIGHTER AIRPLANE MODEL 
WITH A SWEPT-BACK WING AND TAIL. Charles 
P. Morrill, Jr., and Lee E. Boddy. April 14, 1948. 
47p. diagrs., photos. (NACA RM A7K28) 



LONGITUDINAL STABILITY CHARACTERISTICS OF 
A 42° SWEPTBACK WING AND TAIL COMBINATION 
AT A REYNOLDS NUMBER OF 6.8 x 10 6 . Stanley H. 
Spooner and Albert P. Martina. July 22, 1948 
44p. diagrs., photos., 2 tabs. (NACA RM L8E12) 



INVESTIGATION OF THE EFFECTS OF WING AND 
TAIL MODIFICATIONS ON THE LOW-SPEED STA- 
BILITY CHARACTERISTICS OF A Mv>DEL HAVING 
A THIN 40° SWEPT WING OF ASPECT RATIO 3.5. 
Joseph Weil, William C. Sleeman, Jr., and Andrew 
L. Byrnes, Jr. April 1953. 95p. diagrs., photos., 
tab. (NACA RM L53C09) 



WIND-TUNNEL INVESTIGATION AT LOW SPEED 
OF THE EFFECTS OF CHORDWISE WING FENCES 
AND HORIZONTAL-TAIL POSITION ON THE 
STATIC LONGITUDINAL STABIUTY CHARACTER- 
ISTICS OF AN AIRPLANE MODEL WITH A 35° 
SWEPTBACK WING. M. J. Queijo, Byron M. 
Jaquet, and Walter D. Wolhart. 1954. ii, 29p. 
diagrs., photos., tab. (NACA Rept. 1203. Super- 
sedes RM L50K07; RM L51H17) 



36 



( 1 ) AERODYNAMICS 



EFFECTS OF HIGH-LIFT DEVICES AND 
HORIZONTAL -TAIL LOCATION ON THE LOW- 
SPEED CHARACTERISTICS OF A LARGE-SCALE 
45° SWEPT-WING AIRPLANE CONFIGURATION. 
Ralph L. Maki and Ursel R. Embry. August 1954. 
46p. diagrs., photo., tabs. (NACA RM A54E10) 



STATIC LONGITUDINAL STABILITY CHARACTER- 
ISTICS OF A COMPOSITE-PLAN-FORM WING 
MODEL INCLUDING SOME COMPARISONS WITH A 
45° SWEPTBACK WING AT TRANSONIC SPEEDS. 
Walter D. Wolhart. August 1954. 36p. diagrs., 
photo., tabs. (NACA RM L54F24) 



(1. 2.2. 3. 3) 
Leading-Edge Flaps 

A STUDY OF SEVERAL FACTORS AFFECTING THE 
STABILITY CONTRD3UTED BY A HORIZONTAL 
TAIL AT VARIOUS VERTICAL POSITIONS ON A 
SWEPTBACK-WING AIRPLANE MODEL. Gerald V. 
Foster and Roland F. Griner. October 28, 1949. 
28p. diagrs., tab. (NACA RM L9H19) 



LOW-SPEED LONGITUDINAL AND WAKE AIR- 
FLOW CHARACTERISTICS AT A REYNOLDS NUM- 
BER OF 6.0 x 10 6 OF A 52° SWEPTBACK WING 
EQUIPPED WITH VARIOUS SPANS OF LEADING- 
EDGE AND TRAILING-EDGE FLAPS, A FUSELAGE, 
AND A HORIZONTAL TAIL AT VARIOUS VERTICAL 
POSITIONS. Roland F. Griner and Gerald V. Foster. 
February 28, 1951. 66p. diagrs., photo., 3 tabs. 
(NACA RM L50K29) 



LOW-SPEED LONGITUDINAL AND WAKE AIR- 
FLOW CHARACTERISTICS AT A REYNOLDS NUM- 
BER OF 5.5 x 10 6 OF A CIRCULAR-ARC 52° 
SWEPTBACK WING WITH A FUSELAGE AND A 
HORIZONTAL TAIL AT VARIOUS VERTICAL POSI- 
TIONS. Gerald V. Foster and Roland F. Griner. 
June 19, 1951. 44p. diagrs., tabs. 
(NACA RM L51C30) 



EFFECT OF VERTICAL LOCATION OF A HORIZON- 
TAL TAIL ON THE STATIC LONGITUDINAL STA- 
BILITY CHARACTERISTICS OF A 45° SWEPTBACK- 
WING - FUSELAGE COMBINATION OF ASPECT 
RATIO 8 AT A REYNOLDS NUMBER OF 4.0 x 10 6 . 
Relno J. Salmi and William A. Jacques. January 
1952. 42p. diagrs., photos. (NACA RM L51 J08) 



LOW-SPEED LONGITUDINAL CHARACTERISTICS 
OF AN UNSWEPT HEXAGONAL WING WITH AND 
WITHOUT A FUSELAGE AND A HORIZONTAL TAIL 
LOCATED AT VARIOUS POSITIONS AT REYNOLDS 
NUMBERS FROM 2.8 x 10 6 TO 7.6 x 10 6 . Gerald V. 
Foster. Ernst F. Mollenberg, and Robert L. Woods. 
February 26, 1953. 63p. diagrs., photos., 3 tabs. 
(NACA RM L52Lllb) 



LOW-SPEED AILERON EFFECTIVENESS AS 
DETERMINED BY FORCE TESTS AND VISUAL- 
FLOW OBSERVATIONS ON A 52° SWEPTBACK 
WING WITH AND WITHOUT CHORD-EXTENSIONS. 
Patrick A. Cancro. April 1953. 38p. diagrs., 
photos. (NACA RM L53B26) 



INVESTIGATION OF THE EFFECTS OF WING AND 
TAIL MODIFICATIONS ON THE LOW -SPEED STA- 
BILITY CHARACTERISTICS OF A MODEL HAVING 
A THIN 40° SWEPT WING OF ASPECT RATIO 3.5. 
Joseph Weil, William C. Sleeman, Jr., and Andrew 
L. Byrnes, Jr. April 1953. 95p. diagrs., photos., 
tab. (NACA RM L53C09) 



LONGITUDINAL STABILITY AND WAKE-FLOW 
CHARACTERISTICS OF A TWISTED AND 
CAMBERED WING-FUSELAGE COMBINATION OF 
45° SWEEPBACK AND ASPECT RATIO 8 WITH A 
HORIZONTAL TAIL AND STALL-CONTROL DE- 
VICES AT A REYNOLDS NUMBER OF 4.0 x 10 b . 
Gerald V. Foster. June 1953. 51p. diagrs., 
photos., tab. (NACA RM L53D08) 



FREE-FLIGHT -TUNNEL INVESTIGATION OF THE 
LOW-SPEED STABILITY AND CONTROL CHARAC- 
TERISTICS OF A CANARD AIRPLANE MODEL. 
Joseph L. Johnson, Jr., and John W. Paulson. 
October 1953. 37p. diagrs., photo., 2 tabs. (NACA 
RM L53I11) 

EFFECT OF GROUND INTERFERENCE ON THE 
AERODYNAMIC AND FLOW CHARACTERISTICS OF 
A 42° SWEPTBACK WING AT REYNOLDS NUMBERS 
UP TO 6.8 x 10 6 . G. Chester Furlong and Thomas 
V. Bollech. 1955. ii, 60p. diagrs., photos., tab, 
(NACA Rept. 1218. Combination of RM L8G22; 
TN 2487) 

(1. 2. 2.4) 
CONTROLS 

FREE-FLIGHT INVESTIGATION OF THE ROLLING 
EFFECTIVENESS OF SEVERAL DELTA WING - 
AILERON CONFIGURATIONS AT TRANSONIC AND 
SUPERSONIC SPEEDS. Carl A. Sandahl. 
August 27, 1948. 19p. diagrs., photos., tab. 
(NACA RM L8D16) 



LOW-SPEED INVESTIGATION OF THE AERODY- 
NAMIC, CONTROL, AND HINGE-MOMENT CHAR- 
ACTERISTICS OF TWO TYPES OF CONTROLS ON 
A DELTA-WING-FUSELAGE MODEL WITH AND 
WITHOUT NACELLES. William I. Scallion. May 
1953. 47p. diagrs., photos., tabs. 
(NACA RM L53C18) 



(1.2.2.4. 1) 

Flap Type 

FREE-FLIGHT INVESTIGATION OF CONTROL EF- 
FECTIVENESS OF FULL-SPAN, 0.2-CHORD PLAIN 
AILERONS AT HIGH SUBSONIC, TRANSONIC, AND 
SUPERSONIC SPEEDS TO DETERMINE SOME EF- 
FECTS OF WING SWEEPBACK, TAPER, ASPECT 
RATIO, AND SECTION-THICKNESS RATIO. Carl A. 
Sandahl. August 13, 1947. 16p. diagrs., photos., 
tab. (NACA RM L7F30) 



LOW-SPEED WIND-TUNNEL TESTS OF A PILOT - 
LESS AIRCRAFT HAVING HORIZONTAL AND 
VERTICAL WINGS AND CRUCIFORM TAIL. 
N. Mastrocola and A. Assadourian. August 19, 
1947. lOOp. diagrs., photos., tab. 
(NACA RM L6J18a) 



(1) AERODYNAMICS 



37 



ADDITIONAL RESULTS IN A FREE-FLIGHT IN- 
VESTIGATION OF CONTROL EFFECTIVENESS OF 
FULL-SPAN, 0.2-CHORD PLAIN AILERONS AT 
HIGH SUBSONIC, TRANSONIC, AND SUPERSONIC 
SPEEDS TO DETERMINE SOME EFFECTS OF WING 
SWEEPBACK, ASPECT RATIO, TAPER, AND SEC- 
TION THICKNESS RATIO. Carl A. Sandahl and 
H. Kurt Strass. April 23, 1948. 31p. diagrs., 
photos. (NACA RM L7L01) 



EFFECTS OF SWEEP ON CONTROLS. John G. 
Lowry, John A. Axelson, and Harold I. Johnson. 
June 3, 1948. 29p. diagrs. (NACA RM L8A28c) 



FREE-FLIGHT INVESTIGATION OF THE ROLLING 
EFFECTIVENESS AT HIGH SUBSONIC, TRANSONIC, 
AND SUPERSONIC SPEEDS OF LEADING-EDGE 
AND TRAILING-EDGE AILERONS IN CONJUNCTION 
WITH TAPERED AND UNTAPERED PLAN FORMS. 
H. Kurt Strass. July 23, 1948. 19p. diagrs., 
photos. (NACA RM L8E10) 



FREE-FLIGHT INVESTIGATION AT TRANSONIC 
AND SUPERSONIC SPEEDS OF THE ROLLING EF- 
FECTIVENESS OF A THIN, UNSWEPT WING 
HAVING PARTIAL-SPAN AILERONS. Carl A. 
Sandahl. Cctober 22, 1948. 13p. diagrs., photos., 
tab. (NACA RM L8G20a) 



INVESTIGATION OF A THIN WING OF ASPECT 
RATIO 4 IN THE AMES 12-FOOT PRESSURE WIND 
TUNNJEL. IH - THE EFFECTIVENESS OF A 
CONSTANT-CHORD AILERON. Ben H. Johnson, Jr., 
and Fred A. Demele. November 19, 1948. 26p. 
diagrs., photo. (NACA RM A8I17) 



CONTROL EFFECTIVENESS AND HINGE-MOMENT 
MEASUREMENTS AT A MACH NUMBER OF 1.9 OF 
A NOSE FLAP AND TRAILING-EDGE FLAP ON A 
HIGHLY TAPERED LOW-ASPECT-RATIO WING. 
D. William Conner and Mead*. H. Mitchell, ,Tr. 
January 10, 1949. 26p. diagrs.. photo. 
(NACA RML8K17a) 



FREE -FLIGHT INVESTIGATION AT TRANSONIC 
AND SUPERSONIC SPEEDS OF THE ROLLING EF- 
FECTIVENESS OF SEVERAL AILERON CONFIGU- 
RATIONS ON A TAPERED WING HAVING 42.7° 
SWEEPBACK. Carl A. Sandahl. January 11, 1949. 
23p. diagrs., photos., tab. (NACA RM L8K23) 



HINGE-MOMENT MEASUREMENTS OF A WING 
WITH LEADING-EDGE AND TRAILING-EDGE 
FLAPS AT A MACH NUMBER OF 1. 93. William B. 
Boatright and Robert W. Rainey. January 14, 1949. 
12p. diagrs., tab. (NACA RM L8K12a) 



EXPERIMENTAL AND CALCULATED HINGE 
MOMENTS OF TWO AILERONS ON A 42.70 SWEPT - 
BACK WING AT A MACH NUMBER OF 1.9. 
James C. Sivells and Kennith L. Goin. January 19, 
1949. 23p. diagrs., photos., tabs 
(NACA RM L8K24a) 



INVESTIGATION AT A MACH NUMBER OF 1.9 AND 
A REYNOLDS NUMBER OF 2.2 x 10 6 OF SEVERAL 
FLAP-TYPE LATERAL-CONTROL DEVICES ON A 
WING HAVING 42.7° SWEEPBACK OF THE LEAD- 
ING tDGE. Kennith L. Goin. March il, 1949. 
28p. diagrs., photos., tabs. (NACA RM L9A18a) 

WIND-TUNNEL INVESTIGATION OF A TAILLESS 
TRIANGULAR-WING FIGHTER AIRCRAFT AT 
MACH NUMBERS FROM 0.5 TO 1.5. Leslie F. 
Lawrence and James L. Summers. June 24, 1949. 
56p. diagrs., photos., tab, {NACA RM A9B16) 

EFFECTS OF SOME AIRFOIL-SECTION VARIA- 
TIONS ON WING- AILERON ROLLING EFFECTIVE- 
NESS AND DRAG AS DETERMINED IN FREE 
FLIGHT AT TRANSONIC AND SUPERSONIC SPEEDS. 
Carl A. Sandahl, William M. Bland, Jr., and H. Kurt 
Strass. July 22, 1949. 29p. diagrs., photos., tabs. 
(NACARM L9D12) 



THE EFFECT OF SPANWISE AILERON LOCATION 
ON THE ROLLING EFFECTIVENESS OF WINGS 
WITH 0° AND 45° SWEEP AT SUBSONIC, TRAN- 
SONIC, AND SUPERSONIC SPEEDS. H. Kurt Strass. 
April 25, 1950. 28p. diagrs., photo. 
(NACA RM L50A27) 

FREE-FLIGHT INVESTIGATION AT TRANSONIC 
AND SUPERSONIC SPEEDS OF THE ROLLING EF- 
FECTIVENESS OF A PARTIAL-SPAN AILERON ON 
AN INVERSELY TAPERED SWEPTBACK WING. 
H. Kurt Strass, E. M. Fields, and E. D. Schul*. 
May 1, 1950. 17p. diagrs., photo., tabs. 
(NACA RM L50B08) 

THE TRANSONIC CHARACTERISTICS OF A LOW- 
ASPECT-RATIO TRIANGULAR WING WITH A 
CONSTANT-CHORD FLAP AS DETERMINED BY 
WING-FLOW TESTS, INCLUDING CORRELATION 
WITH LARGE-SCALE TESTS. George A. Rathert. 
Jr., L. Stewart Rolls, and Carl M. Hanson. 
July 18, 1950. 39p. diagrs., photo. 
(NACARM A50E10) 



EFFECTS OF VARYING THE SIZE AND LOCATION 
OF TRAILING-EDGE FLAP-TYPE CONTROLS ON 
THE AERODYNAMIC CHARACTERISTICS OF AN UN- 
SWEPT WING AT A MACH NUMBER OF 1.9. Meade 
H. Mitchell, Jr. AugUo. 16, 1950. 33p. diagrs., 
photo., tab. (NACA RM L50F08) 



EXPERIMENTAL DETERMINATION OF EFFECT 
OF STRUCTURAL RIGIDITY ON ROLLING EFFEC- 
TIVENESS OF SOME STRAIGHT AND SWEPT WINGS 
AT MACH NUMBERS FROM 0.7 TO 1.7. H. Kurt 
Strass, E. M. Fields, and Paul E. Purser. 
October 4, 1950. 40p. diagrs., photo., tab. (NACA 
RM L50G14b) 

WIND-TUNNEL INVESTIGATION AT SUBSONIC AND 
LOW TRANSONIC SPEEDS OF THE EFFECTS OF 
AILERON SPAN AND SPANWISE LOCATION ON THE 
ROLLING CHARACTERISTICS OF A TEST VEHICLE 
WITH THREE UNTAPERED 45° SWEPTBACK 
WINGS. HaroldS. Johnson. April 6, 1951. 26p. 
diagrs., photo., tab. (NACA RM L51B16) 

COMPARISONS OF THE EFFECTIVENESS AND 
HINGE MOMENTS OF ALL-MOVABLE DELTA AND 
FLAP-TYPE CONTROLS ON VARIOUS WINGS. 
David G. Stone. April 19, 1951. 13p. diagrs. 
(NACARM L51C22) 



38 



(1) AERODYNAMICS 



SOME EFFECTS OF SPANWISE AILERON LOCA- 
TION AND WING STRUCTURAL RIGIDITY ON THE 
ROLLING EFFECTIVENESS OF 0.3-CHORD FLAP- 
TYPE AILERONS ON A TAPERED WING HAVING 
63° SWEEPBACK AT THE LEADING EDGE AND 
NACA 64A005 AIRFOIL SECTIONS. H. Kurt 
Strass, E. M. Fields, and Eugene D. Schult. 
June 1951. 25p. diagrs., photo., tab. 
(NACA RM L51D18a) 

TESTS IN THE AMES 40- BY 80-FOOT WIND TUN- 
NEL OF AN AIRPLANE CONFIGURATION WITH AN 
ASPECT RATIO 2 TRIANGULAR WING AND AN 
ALL-MOVABLE HORIZONTAL TAIL - LATERAL 
CHARACTERISTICS. David Graham and David G. 
Koenig. February 1952. ■ 38p. diagrs., 2 tabs. 
(NACA RMA51L03) 



LOW-SPEED LATERAL-CONTROL CHARACTER- 
ISTICS OF AN UNSWEPT WING WITH HEXAGONAL 
AIRFOIL SECTIONS AND ASPECT RATIO 2.5 
EQUIPPED WITH SPOILERS AND WITH SHARP- 
ANDTHICKENED-TRAILING-EDGE FLAP-TYPE 
AILERONS AT A REYNOLDS NUMBER OF 7.6 x 10 b . 
James E. Fitzpatrick and Robert L. Woods. April 
1952. 58p. photos., diagrs., tab. 
(NACA RML52B15) 



FREE-FLIGHT INVESTIGATION AT ZERO LIFT IN 
THE MACH NUMBER RANGE BETWEEN 0.7 AND 
1.4 TO DETERMINE THE EFFECTIVENESS OF AN 
INSET TAB AS A MEANS OF AERODYNAMICALLY 
RELIEVING AILERON HINGE MOMENTS. William 
M. Bland, Jr., and Edward T. Marley. January 
1953. 19p. diagrs., photos. (NACA RM L52K07) 



TESTS IN THE AMES 40- BY 80-FOOT WIND TUN- 
NEL OF AN AIRPLANE MODEL WITH AN ASPECT 
RATIO 4 TRIANGULAR WING AND AN ALL- 
MOVABLE HORIZONTAL TAIL - HIGH-LIFT DE- 
VICES AND LATERAL CONTROLS. Ralph W. 
Franks. February 1953. 45p. diagrs., photo., 2 
tabs. (NACA RM A52K13) 



TESTS IN THE AMES 40- BY 80-FOOT WIND TUN- 
NEL OF TWO AIRPLANE MODELS HAVING AS- 
PECT RATIO 2 TRAPEZOIDAL WINGS OF TAPER 
RATIOS 0.33 AND 0.20. Ralph W. Franks. 
February 1953. 56p. diagrs., photos., 3 tabs. 
(NACA RMA52L16) 



TESTS IN THE AMES 40- BY 80-FOOT WIND TUN- 
NEL OF AN AIRPLANE CONFIGURATION WITH AN 
ASPECT RATIO 3 TRIANGULAR WING AND AN 
ALL-MOVABLE HORIZONTAL TAIL - LONGITU- 
DINAL AND LATERAL CHARACTERISTICS. David 
G. Koenig. April 1953. 61p. diagrs., photos., 
4 tabs. (NACA RM A52L15) 



LOW-SPEED AILERON EFFECTIVENESS AS 
DETERMINED BY FORCE TESTS AND VISUAL- 
FLOW OBSERVATIONS ON A 52° SWEPTBACK 
WING WITH AND WITHOUT CHORD-EXTENSIONS. 
Patrick A. Cancro. April 1953. 38p. diagrs.', 
photos. (NACA RM L53B26) 



THE EFFECT AT HIGH SUBSONIC SPEEDS OF A 
FLAP-TYPE AILERON ON THE CHORDWISE PRES- 
SURE DISTRIBUTION NEAR MIDSEMISPAN OF A 
TAPERED 35° SWEPTBACK WING OF ASPECT 
RATIO 4 HAVING NACA 65A006 AIRFOIL SECTION. 
Alexander D. Hammond and Barbara M. Keffer. 
May 1953. 89p. diagrs., tab. (NACA RM L53C23) 



AILERON AND ELEVATOR HINGE MOMENTS OF 
THE BELL X-l AIRPLANE MEASURED IN TRAN- 
SONIC FLIGHT. Hubert M. Drake and John B. 
McKay. June 1953. 27p. diagrs. 
(NACA RM L53E04) 

THE LATERAL CONTROL CHARACTERISTICS OF 
CONSTANT-PERCENT-CHORD TRAILING-EDGE 
ELEVONS ON A POINTED WING OF ASPECT RATIO 
2 AT MACH NUMBERS UP TO 0.95. Vertin D. Reed 
and Donald W. Smith. August 1953. 105p. diagrs., 
photo., tabs. (NACA RM A53F03) 

SOME EFFECTS OF AEROELASTICITY AND 
SWEEPBACK ON THE ROLLING EFFECTIVENESS 
AND DRAG OF A 1 11-SCALE MODEL OF THE 
BELL X-5 AIRPLANE WING AT MACH NUMBERS 
FROM 0.6 TO 1.5. Roland D. English. November 
1953. 21p. diagrs., photos. (NACA RM L53I18b) 

CHORDWISE PRESSURES AND SECTION FORCE 
AND MOMENT COEFFICIENTS AT HIGH SUBSONIC 
SPEEDS NEAR MIDSPAN OF A TAPERED 35° 
SWEPTBACK WING WITH A FLAP-TYPE CONTROL 
AND AN ATTACHED TAB. Alexander D. Hammond 
and Barbara M. Keffer. March 1954. 57p. diagrs., 
35 tabs. (NACA RM L54A22) 

HINGE-MOMENT, LIFT, AND PITCHING-MOMENT 
CHARACTERISTICS OF A FLAP-TYPE CONTROL 
SURFACE HAVING VARIOUS HINGE- LINE LOCA- 
TIONS ON A 4-PERCENT-THICK 60° DELTA WING. 
TRANSONIC -BUMP METHOD. Robert F. Thompson 
March 1954. 73p. diagrs., photo. 
(NACA RM L54B08) 

COMPARISON BETWEEN THEORETICAL AND EX- 
PERIMENTAL RATES OF ROLL OF TWO MODELS 
WITH FLEXIBLE RECTANGULAR WINGS AT SU- 
PERSONIC SPEEDS." John M. Hedgepeth and 
Robert J. Kell. August 1954. 21p. diagrs., photo., 
tabs. (NACA RM L54F23) 

SOME EFFECTS OF EXTERNAL WING TIP STORES 
ON THE ROLLING EFFECTIVENESS AND DRAG OF 
PLAIN AND HALF-DELTA TIP AILERONS ON A 
4-PERCENT-THICK, TAPERED, UNSWEPT WING. 
Roland D. English. August 1954. 14p. diagrs., 
photos., tab. (NACA RM L54F29a) 



CALCULATED SPANWISE LIFT DISTRIBUTIONS, 
INFLUENCE FUNCTIONS, AND INFLUENCE COEF- 
FICIENTS FOR UNSWEPT WINGS IN SUBSONIC 
FLOW. Franklin W. Diederich and Martin Zlotnick. 
1955. ii, 69p. diagrs., tabs. (NACA Rept. 1228. 
Supersedes TN 3014) 

SUMMARY OF RESULTS OF A WIND-TUNNEL 
INVESTIGATION OF NINE RELATED HORIZONTAL 
TAILS. Jules B. Dods, Jr. and Bruce E. Tinling. 
July 1955. 105p. diagrs., 2 tabs. (NACA TN 3497. 
Formerly RM A51G31a) 

THEORETICAL ANALYSES TO DETERMINE 
UNBALANCED TRAILING-EDGE CONTROLS 
HAVING MINIMUM HINGE MOMENTS DUE TO 
DEFLECTION AT SUPERSONIC SPEEDS. Kennith L. 
Goin. August 1955.52p. diagrs., tab. (NACA TN 3471. 
Formerly RM L51F19) 

CALCULATED SPANWISE LIFT DISTRIBUTIONS 
AND AERODYNAMIC INFLUENCE COEFFICIENTS 
FOR SWEPT WINGS IN SUBSONIC FLOW. 
Franklin W. Diederich and Martin Zlotnick. 
October 1955. 173p. diagrs., tabs. (NACA 
TN 3476) 



39 



(1) AERODYNAMICS 



THEORETICAL ANALYSIS OF LINKED LEADING- 
EDGE AND TRAILING- EDGE FLAP-TYPE CON- 
TROLS AT SUPERSONIC SPEEDS. E. Carson 
Yates, Jr.* March 1956. 40p. diagrs., tab. 
(NACA TN3617) 



INVESTIGATION BY THE TRANSONIC -BUMP 
METHOD OF A 35° SWEPTBACK SEMISPAN 
MODEL EQUIPPED WITH A FLAP OPERATED BY 
A SERIES OF SERVOVANES LOCATED AHEAD OF 
AND GEARED TO THE FLAP. William H. Phillips 
and Robert F. Thompson. April 1956. 39p. diagrs., 
photo. (NACA TN 3689. Supersedes RM L51J10) 



A WIND-TUNNEL INVESTIGATION OF A 0.4-SCALE 
MODEL OF AN ASSAULT-TRANSPORT AIRPLANE 
WITH BOUNDARY-LAYER CONTROL APPLIED. 
Marvin P. Fink, Bennie W. Cocke, and Stanley 
Lipson. May 1956. 63p. diagrs., photos. 
(NACA RM L55G26a) 



(1- 2. 2.4. 2) 
Spoilers 



LONGITUDINAL STABILITY AND CONTROL CHAR- 
ACTERISTICS OF A SEMISPAN WIND-TUNNEL 
MODEL OF A TAILLESS AIRPLANE AND A COM- 
PARISON WITH COMPLETE -MODEL WIND-TUNNEL 
TESTS AND SEMISPAN-MODEL WING-FLOW TESTS. 
Kenneth W. Goodson and Thomas J. King, Jr. 
October 10, 1949. 63p. diagrs., photos. 
vNACA RM LGC31) 



LOW-SPEED LATERAL-CONTROL CHARACTER- 
ISTICS OF AN UNSWEPT WING WITH HEXAGONAL 
AIRFOIL SECTIONS AND ASPECT RATIO 2.5 
EQUIPPED WITH SPOILERS AND WITH SHARP- 
AND THICKENED-TRAILING-EDGE FLAP-TYPE 
AILERONS AT A REYNOLDS NUMBER OF 7.6 x 10 6 . 
James E. Fitzpatrick and Robert L. Woods. April 
1952. 58p. photos., diagrs., tab. 
(NACA RM L52B15) 



CHORDWISE PRESSURE DISTRIBUTION AT HIGH 
SUBSONIC SPEEDS NEAR MIDSEMISPAN OF A 
TAPERED 35° SWEPTBACK WING OF ASPECT 
RATIO 4 HAVING NACA 65A006 AIRFOIL SECTIONS 
AND EQUIPPED WITH VARIOUS SPOILER AILER- 
ONS. Alexander D. Hammond and Barbara M. 
McMullan, June 1952. 76p. diagrs., tabs. 
(NACA RM L52C28) 



WIND-TUNNEL INVESTIGATION AT HIGH SUB- 
SONIC SPEEDS OF A SPOILER-SLOT-DEFLECTOR 
COMBINATION ON AN NACA 65A006 WING WITH 
QUARTER-CHORD LINE SWEPT BACK 32.6°. 
Raymond D. Vogler. May 1953. 24p. diagrs. 
(NACA RM L53D17) 



LOW-SPEED WIND-TUNNEL INVESTIGATION OF A 
JET CONTROL ON A 35° SWEPT WING. John G. 
Lowry and Thomas R. Turner. October 1953. 9p. 
diagrs. (NACA RM L53I09a) 



EFFECT AT TRANSONIC SPEEDS OF INBOARD 
SPOILERS ON THE STATIC LONGITUDINAL STA- 
BILITY CHARACTERISTICS OF A 45° SWEPTBjACK 
WING-BODY COMBINATION HAVING A LEADING- 
EDGE CHORD-EXTENSION. James H. Henderson. 
June 1954. 24p. diagrs., photo. 
(NACA RM L54D13) 



INVESTIGATION BY THE TRANSONIC-BUMP 
MEfHOD OF A 35° SWEPTBACK SEMISPAN 
MODEL EQUIPPED WITH A FLAP OPERATED BY 
A SERIES OF SERVOVANES LOCATED AHEAD OF 
AND GEARED TO THE FLAP. William H. Phillips 
and Robert F. Thompson. April 1956. 39p. diagrs., 
photo. (NACA TN 3689. Supersedes RM L51J10) 



AN INVESTIGATION OF FORWARD-LOCATED 
FIXED SPOILERS AND DEFLECTORS AS GUST 
ALLEVIATORS ON AN UNSWEPT-WING MODEL. 
Delwin R. Croom, C. C. Shufflebarger, and 
Jarrett K. Huffman. June 1956. 26p. diagrs., 
photo. (NACA TN 3705) 



(1. 2. 2.4. 3) 
All Movable 

ROLLING EFFECTIVENESS OF ALL-MOVABLE 
WINGS AT SMALL ANGLES OF INCIDENCE AT 
MACH NUMBERS FROM 0.6 TO 1.6. H. Kurt 
Strass and Edward T. JVlarley. October 1951. 16p. 
diagrs., photo., tab. (NACA RM L51H03) 



THE STATIC LONGITUDINAL CHARACTERISTICS 
AT MACH NUMBERS UP TO 0.95 OF A 
TRIANGULAR-WING CANARD MODEL HAVING A 
TRLANGULAF CONTROL. .Tack D. Stephenson and 
Ralph Selan. December 1951. 72p. diagrs., photo. 
(NACA RM A51I07) 



TESTS IN THE AMES 40- BY 80-FOOT WIND TUN- 
NEL OF AN AIRPLANE CONFIGURATION WITH AN 
ASPECT RATIO 2 TRIANGULAR WING AND AN 
ALL-MOVABLE HORIZONTAL TAIL - LATERAL 
CHARACTERISTICS. David Graham and David G. 
Koenig. February 1952. 38p. diagrs., 2 tabs. 
(NACA RM A51L03) 



AN APPROXIMATION TO THE EFFECT OF GEO- 
METRIC DIHEDRAL ON THE ROLLING MOMENT 
DUE TO SIDESLIP FOR WINGS AT TRANSONIC AND 

SUPERSONIC SPEEDS. Paul E. Purser. April 
1952. lOp. diagrs. (NACA RM L52B01) 



TESTS IN THE AMES 40- BY 80-FOOT WIND TUN- 
NEL OF AN AIRPLANE CONFIGURATION WITH AN 
ASPECT RATIO 3 TRIANGULAR WING AND AN 
ALL-MOVABLE HORIZONTAL TAIL - LONGITU- 
DINAL AND LATERAL CHARACTERISTICS. David 
G. Koenig. April 1953. 61p. diagrs., photos., 
4 tabs. (NACA RM A52L15) 



TESTS IN THE AMES 40- BY 80-FOOT WIND TUN- 
NEL OF AN AIRPLANE CONFIGURATION WITH A 
VARIABLE-INCIDENCE TRIANGULAR WING AND 
AN ALL-MOVABLE HORIZONTAL TAIL. David G. 

Koenig. June 1953, 42p. diagrs., photo., tabs. 
(NACARM A53D21) 



40 



(1) AERODYNAMICS 



LARGE-SCALE LOW -SPEED WIND-TUNNEL TESTS 
OF A MODEL HAVING A 60° DELTA HORIZONTAL 
CANARD CONTROL SURFACE AND WING TO OB- 
TAIN STATIC-LONGITUDINAL-STABILITY AND 
CANARD-SURFACE HINGE-MOMENT,DATA. 
Dale L. Burrows. June 1954. 21p. diagr8. 
(NACA RM L54D16a) 



SOME EFFECTS OF EXTERNAL WING TIP STORES 
ON THE ROLLING EFFECTIVENESS AND DRAG OF 
PLAIN AND HALF-DELTA TIP AILERONS ON A 
4-PERCENT-THICK, TAPERED, UNSWEPT WING. 
Roland D. English. August 1954. 14p. diagrs., 
photos., tab. (NACA RM L54F29a) 



(1. 2. 2. 5) 
REYNOLDS NUMBER EFFECTS 



EFFECTS OF SWEEP ON CONTROLS. John G. 
Lowry, John A. Axelson, and Harold I. Johnson. 
June 3, 1948. 29p. diagrs. (NACA RM L8A28c) 



THE TRANSONIC CHARACTERISTICS OF A LOW- 
ASPECT-RATIO TRIANGULAR WING WITH A 
CONSTANT-CHORD FLAP AS DETERMINED BY 
WING-FLOW TESTS, INCLUDING CORRELATION 
WITH LARGE-SCALE TESTS. George A. Rathert, 
Jr., L. Stewart Rolls, and Carl M. Hanson. 
July 18, 1950. 39p. diagrs., photo. 
(NACA RM A50E10) 



CHARACTERISTICS THROUGHOUT THE SUBSONIC 
SPEED RANGE OF A PLANE WING AND OF A 
CAMBERED AND TWISTED WING, BOTH HAVING 
45° OF SWEEPBACK. Ben H. Johnson, Jr., and 
Harry H. Shibata. July 1951. 122p. diagrs.. 
photos. (NACA RM A51D27) 



THE EFFECTS OF REYNOLDS NUMBER AT MACH 
NUMBERS UP TO 0.94 ON THE LOADING ON A 35° 
SWEPTBACK WING HAVING NACA 65^012 
STREAMWISE SECTIONS. Bruce E. Tinling and 
Armando E. Lopez. June 1952. 115p. diagrs., 
photos., tabs. (NACA RM A52B20) 



AN INVESTIGATION THROUGHOUT THE SUBSONIC 
SPEED RANGE OF A FULL-SPAN AND A SEMI- 
SPAN MODEL OF A PLANE WING AND OF A 
CAMBERED AND TWISTED WING, ALL HAVING 
45° OF SWEEPBACK. Harry H. Shibata, Angelo 
Bandettini, and Joseph Cleary. June 1952. 65p. 
diagrs., photos. (NACA RM A52D01) 



THE LONGITUDINAL CHARACTERISTICS AT MACH 
NUMBERS UP TO 0.92 OF A CAMBERED AND 
TWISTED WING HAVING 40° OF SWEEPBACK AND 
AN ASPECT RATIO OF 10. George G. Edwards, 
Bruce E. Tinling, and Arthur C. Ackerman. 
September 1952. 71p, diagrs., photos., tab. 
(NACA RM A52F18) 



PRESSURE DISTRIBUTION AT MACH NUMBERS UP 
TO 0.90 ON A CAMBERED AND TWISTED WING 
HAVING 40° OF SWEEPBACK AND AN ASPECT 
RATIO OF 10, INCLUDING THE EFFECTS OF 
FENCES. Frederick W. Boltz and Harry H. 
Shibata. March 1953. 133p. diagrs., photos., tabs. 
(NACA RM A52K20) 



WIND-TUNNEL INVESTIGATION OF STALL CON- 
TROL BY SUCTION THROUGH A POROUS LEADING 
EDGE ON A 37° SWEPTBACK WING OF ASPECT 
RATIO 6 AT REYNOLDS NUMBERS FROM 2.50 xlO 6 
to 8.10 x 10 6 . Robert R. Graham and William A. 
Jacques. March 1953. 67p. diagrs., photo., 2 tabs. 
(NACARML52L05) 



THE EFFECTS OF LEADING-EDGE EXTENSIONS, 
A TRAILING-EDGE EXTENSION, AND A FENCE 
ON THE STATIC LONGITUDINAL STABILITY OF A 
WTNG-FUSELAGE-TAIL COMBINATION HAVING 
A WING WITH 35° OF SWEEPBACK AND AN AS- 
PECT RATIO OF 4.5. Ralph Selan and Angelo 
Bandettini. August 1953. 81p. diagrs., photos., 
tabs. (NACA RM A53E12) 



THE LATERAL CONTROL CHARACTERISTICS OF 
CONSTANT-PERCENT-CHORD TRAILING-EDGE 
ELEVONS ON A POINTED WING OF ASPECT RATIO 
2 AT MACH NUMBERS UP TO 0.95. Verlln D. Reed 
and Donald W. Smith. August 1953. 105p. diagrs., 
photo., tabs. (NACA RM A53F03) 



EFFECT OF REDUCTION IN THICKNESS FROM 6 
TO 2 PERCENT AND REMOVAL OF THE POINTED 
TIPS ON THE SUBSONIC STATIC LONGITUDINAL 
STABILITY CHARACTERISTICS OF A 60° TRIANGU- 
LAR WING IN COMBINATION WITH A FUSELAGE. 
William E. Palmer. August 1953. 44p. diagrs., 
photo., tab. (NACA RM L53F24) 



WIND-TUNNEL INVESTIGATION AT HIGH AND LOW 
SUBSONIC MACH NUMBERS OF TWO UNSWEPT 
WINGS HAVING NACA 2-006 AND NACA 65A006 
AIRFOIL SECTIONS. Stanley F. Racisz. 
December 1953. 40p. diagrs., photo., tab. 
(NACA RM L53J29) 



THE EFFECTS OF HORIZONTAL -TAIL HEIGHT 
AND A PARTIAL-SPAN LEADING-EDGE EXTEN- 
SION ON THE STATIC LONGITUDINAL STABILITY 
OF A WING- FUSELAGE -TAIL COMBINATION 
HAVING A SWEPTBACK WING. Angelo Bandettini 
and Ralph Selan. March 1954. 54p. diagrs., 
photos., 2 tabs. (NACA RM A53J07) 



SUBSONIC INVESTIGATION OF EFFECTS OF BODY 
INDENTATION ON ZERO-LIFT DRAG CHARACTER- 
ISTICS OF A 450 SWEPTBACK WING-BODY COMBI- 
NATION WITH NATURAL AND FIXED BOUNDARY- 
LAYER TRANSITION THROUGH A RANGE OF 
REYNOLDS NUMBER FROM 1 x 10 b TO 8 x 10 6 . 
Gene J. Bingham and Albert L. Braslow. April 1954. 
[Op. diagrs., photos. (NACA RM L54B18a) 



EFFECT OF GROUND INTERFERENCE ON THE 
AERODYNAMIC AND FLOW CHARACTERISTICS OF 
A 42° SWEPTBACK WING AT REYNOLDS NUMBERS 
UP TO 6.8 x 10 6 . G. Chester Furlong and Thomas 
V. Bollech. 1955. ii, 60p. diagrs., photos., tab. 
(NACA Rept. 1218. Combination of RM L8G22; 
TN 2487) 



41 



(1 ) AERODYNAMICS 



(1.2.2. 6) 
MACH NUMBER EFFECTS 



FREE-FLIGHT INVESTIGATION OF CONTROL EF- 
FECTIVENESS OF FULL-SPAN, 0.2-CHORD PLAIN 
AILERONS AT HIGH SUBSONIC, TRANSONIC, AND 
SUPERSONIC SPEEDS TO DETERMINE SOME EF- 
FECTS OF WING SWEEPBACK, TAPER, ASPECT 
RATIO, AND SECTION-THICKNESS RATIO. Carl A. 
Sandaht. August 13, 1947. 16p. diagrs., photos., 
tab, (NACA RM L7F30) 



FLIGHT INVESTIGATION TO DETERMINE THE 
HINGE MOMENTS OF A BEVELED-EDGE AILERON 
ON A 45° SWEPTBACK WING AT TRANSONIC AND 
LOW SUPERSONIC SPEEDS. William N. Gardner 
and Howard J. Curfman, Jr. November 12, 1947. 
20p. diagrs., photos. (NACA RM L7H26) 



THE HIGH-SPEED AERODYNAMIC EFFECTS OF 
MODIFICATIONS TO THE WING AND WING- 
FUSELAGE INTERSECTION OF AN AIRPLANE 
MODEL WITH THE WING SWEPT BACK 35°, Lee 
E. Boddy and Charles P. Morrill, Jr. February 18, 
1948. 34p. diagrs., photos. (NACA RM A7J02) 



HIGH-SPEED STABILITY AND CONTROL CHARAC- 
TERISTICS OF A FIGHTER AIRPLANE MODEL 
WITH A SWEPT-BACK WING AND TAIL. Charles 
P. Morrill, Jr., and Lee E. Boddy. April 14, 1948. 
47p. diagrs., photos. (NACA RM A7K28) 

THE AERODYNAMIC FFFF.CTS OF ROCKETS AND 
FUEL TANKS MOUNTED UNDER THE SWEPT- 
BACK WING OF AN AIRPLANE MODEL. Lee E. 
Boddy and Charles P. Morrill. Jr. April 23. 1948. 
19p. diagrs. (NACA RM A7J03) 



ADDITIONAL RESULTS IN A FREE-FLIGHT IN- 
VESTIGATION OF CONTROL EFFECTIVENESS OF 
FULL-SPAN, 0.2-CHORD PLAIN AILERONS AT 
HIGH SUBSONIC, TRANSONIC, AND SUPERSONIC 
SPEEDS TO DETERMINE SOME EFFECTS OF WING 
SWEEPBACK, ASPECT RATIO, TAPER, AND SEC- 
TION THICKNESS RATIO. Carl A. Sandahl and 
H. Kurt Strass. April 23, 1948. 31p. diagrs., 
photos. (NACA RM L7L01) 



EFFECTS OF SWEEP ON CONTROLS. John G. 
Lowry, John A. Axelson, and Harold I. Johnson. 
June 3, 1948. 29p. diagrs. (NACA RM L8A28c) 

FREE- FLIGHT INVESTIGATION OF THE ROLLING 
EFFECTIVENESS AT HIGH SUBSONIC, TRANSONIC, 
AND SUPERSONIC SPEEDS OF LEADING-EDGE 
AND TRAILING- EDGE AILERONS IN CONJUNCTION 
WITH TAPERED AND UNTAPERED PLAN FORMS. 
H. Kurt Strass. July 23, 1948. 19p. diagrs., 
photos. (NACA RM L8E10) 



FREE-FLIGHT INVESTIGATION OF THE ROLLING 
EFFECTIVENESS OF SEVERAL DELTA WING - 
AILERON CONFIGURATIONS AT TRANSONIC AND 
SUPERSONIC SPEEDS. Carl A. Sandahl. 
August 27, 1948. 19p. diagrs., photos., tab. 
(NACA RM L8D16) 



PRELIMINARY RESULTS OF NACA TRANSONIC 
FLIGHTS OF THE XS-1 AIRPLANE WITH 10- 
PERCENT-THICK WING AND 8-PERCENT-THICK 
HORIZONTAL TAIL. Hubert M. Drake, Harold R, 
Goodman, and Herbert H. Hoover. October 13, 1948. 
18p. diagrs., photos. (NACA RM L8I29) 



FREE-FLIGHT INVESTIGATION AT TRANSONIC 
AND SUPERSONIC SPEEDS OF THE ROLLING EF- 
FECTIVENESS OF A THIN, UNSWEPT WING 
HAVING PARTIAL-SPAN AILERONS. Carl A. 
Sandahl. October 22, 1948. 13p. diagrs., photos., 
tab. (NACA RM L8G20a) 



INVESTIGATION OF A THIN WING OF ASPECT 
RATIO 4 IN THE AMES 12-FOOT PRESSURE WIND 
TUNNEL, m - THE EFFECTP/ENESS OF A 
CONSTANT-CHORD AILERON. Ben H. Johnson, Jr. , 
and Fred A, Demele. November 19, 1948. 26p. 
diagrs,, photo. (NACA RM A8I17) 



FREE-FLIGHT INVESTIGATION AT TRANSONIC 
AND SUPERSONIC SPEEDS OF THE ROLLING EF- 
FECTIVENESS OF SEVERAL AILERON CONFIGU- 
RATIONS ON A TAPERED WING HAVING 42.7° 
SWEEPBACK. Carl A, Sandahl. January 11, 1949. 
23p. diagrs., photos., tab. (NACA RM L8K23) 



HIGH-SPEED WIND-TUNNEL INVESTIGATION OF 
A SWEPTBACK WING WITH AN ADDED TRIANGU- 
LAR AREA AT THE CENTER. Beverly Z. Henry, 



(NACA RM L8J12) 



WIND-TUNNEL INVESTIGATION OF A TAILLESS 
TRIANGULAR-WING FIGHTER AIRCRAFT AT 
MACH NUMBERS FROM 0.5 TO 1.5. Leslie F. 
Lawrence and James L. Summers. June 24, 1949. 
56p. diagrs., photos., tab. (NACA RM A9B16) 



EFFECTS OF SOME AIRFOIL-SECTION VARIA- 
TIONS ON WING-AILERON ROLLING EFFECTIVE- 
NESS AND DRAG AS DETERMINED IN FREE 
FLIGHT AT TRANSONIC AND SUPERSONIC SPEEDS. 
Carl A. Sandahl, William M. Bland, Jr., and H. Kurt 
Strass. July 22, 1949. 29p. diagrs., photos., tabs. 
(NACA RM L9D12) 



AERODYNAMIC CHARACTERISTICS AND FLYING 
QUALITIES OF A TAILLESS TRIANGULAR-WING 
AIRPLANE CONFIGURATION AS OBTAINED FROM 
FLIGHTS OF ROCKET-PROPELLED MODELS AT 
TRANSONIC AND LOW SUPERSONIC SPEEDS. 
Grady L. Mite ham, Joseph E. Stevens, and Harry P. 
Norris. February 9, 1950. 67p. diagrs., photos., 
tabs. (NACA RM L9L07) 



THE EFFECT OF SPANWISE AILERON LOCATION 
ON THE ROLLING EFFECTIVENESS OF WINGS 
WITH 0° AND 45° SWEEP AT SUBSONIC, TRAN- 
SONIC, AND SUPERSONIC SPEEDS. H. Kurt Strass. 
April 25, 1950. 28p. diagrs., photo. 
(NACA RM L50A27) 



FREE-FLIGHT INVESTIGATION AT TRANSONIC 
AND SUPERSONIC SPEEDS OF THE ROLLING EF- 
FECTIVENESS OF A PARTIAL-SPAN AILERON ON 
AN INVERSELY TAPERED SWEPTBACK WING. 
H. Kurt Strass, E. M. Fields, and E. D. Schult. 
Mayl, 1950. 17p. diagrs., photV, tabs. 
(NACA RM L50B08) 



42 



(1) AERODYNAMICS 



WING-DROPPING CHARACTERISTICS OF SOME 
STRAIGHT AND SWEPT WINGS AT TRANSONIC 
SPEEDS AS DETERMINED WITH ROCKET- 
POWERED MODELS. David G. Stone. May 26, 

1950. 12p. diagrs.. tab. (NACA RM L50C01) 



THE TRANSONIC CHARACTERISTICS OF A LOW- 
ASPECT-RATIO TRIANGULAR WING WITH A 
CONSTANT-CHORD FLAP AS DETERMINED BY 
WING-FLOW TESTS, INCLUDING CORRELATION 
WITH LARGE-SCALE TESTS. George A. Rathert, 
Jr., L. Stewart Rolls, and Carl M. Hanson. 
July 18, 1950. 39p. diagrs., photo. 
(NACA RM A50E10) 



EXPERIMENTAL INVESTIGATION OF VARIOUS 
WING-MOUNTED EXTERNAL STORES ON A WING- 
FUSELAGE COMBINATION HAVING A SWEPTBACK 
WING OF INVERSE TAPER RATIO. Kenneth P. 
Spreemann and H. Norman Silvers. September 15, 
1950. 29p. diagrs., photos., tab. (NACA RM L9J06) 



EXPERIMENTAL DETERMINATION OF EFFECT 
OF STRUCTURAL RIGIDITY ON ROLLING EFFEC- 
TIVENESS OF SOME STRAIGHT AND SWEPT WINGS 
AT MACH NUMBERS FROM 0.7 TO 1.7. H. Kurt 
Strass, E. M. Fields, and Paul E. Purser. 
October 4, 1950. 40p. diagrs., photo., tab. (NACA 
RM L50G14D) 



A TRANSONIC-WING INVESTIGATION IN THL 
LANGLEY 8-FOOT HIGH-SPEED TUNNEL AT HIGH 
SUBSONIC MACH NUMBERS AND AT A MACH 
NUMBER OF 1.2. WING-FUSELAGE CONFIGURA- 
TION WITH A WING OF 45° SWEEPBACK, ASPECT 
RATIO 4, TAPER RATIO 0.6, AND NACA 65A006 
AIRFOIL SECTION. Robert S. Osborne. 
October 10, 1950. 49p. diagrs., photos. 
(NACA RM L50H08) 



TABULATED PRESSURE COEFFICIENTS AND 
AERODYNAMIC CHARACTERISTICS MEASURED ON 
THE WING OF THE BELL X-l AIRPLANE IN PULL- 
UPS AT MACH NUMBERS FROM 0.53 TO 0.99. 
Ronald J. Knapp and Gertrude V. Wilken. 
November 1, 1950. 77p. diagrs., photo., 11 tabs. 
(NACA RM L50H28) 



A TRANSONIC WING INVESTIGATION IN THE 
LANGLEY 8-FOOT HIGH-SPEED TUNNEL AT HIGH 
SUBSONIC MACH NUMBERS AND AT A MACH 
NUMBER OF 1.2. WING-FUSELAGE CONFIGURA- 
TION HAVING A WING OF 35° SWEEPBACK, AS- 
PECT RATIO 4, TAPER RATIO 0.6, AND NACA 
65A006 AIRFOIL SECTION. Beverly Z. Henry, Jr. 
November 15, 1950. 40p. diagrs., photo., tab 
(NACA RM L50J09) 



A TRANSONIC -WING INVESTIGATION IN THE 
LANGLEY 8-FOOT HIGH-SPEED TUNNEL AT HIGH 
SUBSONIC MACH NUMBERS AND AT A MACH NUM- 
BER OF 1.2. WING-FUSELAGE CONFIGURATION 
HAVING A WING OF 60° SWEEPBACK, ASPECT 
RATIO 4, TAPER RATIO 0.6, AND NACA 65A006 
AIRFOIL SECTION. Raymond B. Wood and Frank F. 
Fleming. January 24, 1951. 43p. diagrs., photo. 
(NACA RM L50J25) 



AERODYNAMIC CHARACTERISTICS INCLUDING 
PRESSURE DISTRIBUTIONS OF A FUSELAGE AND 
THREE COMBINATIONS OF THE FUSELAGE WITH 
SWEPT-BACK WINGS AT HIGH SUBSONIC SPEEDS. 
Fred B. Sutton and Andrew Martin. February 6, 
1951. 117p. diagrs., photos., tabs. 
(NACA RM A50J26a) 

PRELIMINARY FLIGHT INVESTIGATION OF THE 

MANEUVERING ACCELERATIONS AND BUFFET 
BOUNDARY OF A 35° SWEPT - ,VING AIRPLANE AT 
HIGH ALTITUDE AND TRANSONIC SPEEDS. 
George A. Rathert, Jr., Howard L. Ziff, and George 
E. Cooper. February 21, 1951. 12p. diagrs., 
Dhoto., tab. (NACA RM A50L04) 



INVESTIGATION OF THE EFFECTS OF GEO- 
METRIC CHANGES IN AN UNDERWING PYLON - 
SUSPENDED EXTERNAL -STORE INSTALLATION 
ON THE AERODYNAMIC CHARACTERISTICS OF A 
45° SWEPTBACK WING AT HIGH SUBSONIC 
SPEEDS. Kenneth P. Spreemann and William J. 
Alford, Jr. March 5, 1951. 91p. diagrs., photos., 
tabs. (NACA RML50L12) 



A TRANSONIC -WING INVESTIGATION IN THE 
LANGLEY 8-FOOT HIGH-SPEED TUNNEL AT 
HIGH SUBSONIC MACH NUMBERS AND AT A 
MACH NUMBER OF 1.2. WING-FUSELAGE CON- 
FIGURATION HAVING A WING OF 0° SWEEPBACK, 
ASPECT RATIO 4/0, TAPER RATIO 0.6, AND NACA 
65A006 AIRFOIL SECTION. Maurice S. Cahn and 
Carroll R. Bryan. March 6, 1951. 37p, diagrs., 
photos. (NACA RM L51A02) 



WIND-TUNNEL INVESTIGATION AT SUBSONIC AND 
LOW TRANSONIC SPEEDS OF THE EFFECTS OF 
AILERON SPAN AND SPANWISE LOCATION ON THE 
ROLLING CHARACTERISTICS OF A TEST VEHICLE 
WITH THREE UNTAPERED 45° SWEPTBACK 
WINGS. HaroldS. Johnson. April 6, 1951. 26p. 
diagrs., photo., tab. (NACA RM L51B16) 



COMPARISONS OF THE EFFECTIVENESS AND 
HINGE MOMENTS OF ALL-MOVABLE DELTA AND 
FLAP-TYPE CONTROLS ON VARIOUS WINGS. 
David G. Stone. April 19, 1951. 13p. diagrs. 
(NACARM L51C22) 



A COMPARISON OF THE EXPERIMENTAL AND 
THEORETICAL LOADING OVER TRIANGULAR 
WINGS IN SIDESLIP AT SUPERSONIC SPEEDS. 
John W. Boyd. May 18, 1951. 58p. diagrs., photo., 
tabs. (NACA RM A51C13) 



REVIEW OF SOME RECENT DATA ON BUFFET 
BOUNDARIES. Paul E. Purser and John A. Wyss. 
May 23, 1951. lip. diagrs. (NACA RM L51E02a) 



SOME EFFECTS OF SPANWISE AILERON LOCA- 
TION AND WING STRUCTURAL RIGIDITY ON THE 
ROLLING EFFECTP7ENESS OF 0.3-CHORD FLAP- 
TYPE AILERONS ON A TAPERED WING HAVING 
63° SWEEPBACK AT THE LEADING EDGE AND 
NACA 64A005 AIRFOIL SECTIONS. H. Kurt 
Strass, E. M. Fields, and Eugene D. Schult. 
June 1951. 25p. diagrs., photo., tab. 
(NACA RM L51D18a) 



43 



(1) AERODYNAMICS 



AERODYNAMIC CHARACTERISTICS OF FOUR 
WINGS OF SWEEPBACK ANGLES 0°, 35°, 45°, AND 
60°, NACA 65A006 AIRFOIL SECTION, ASPECT 
RATIO 4, AND TAPER RATIO 0.6 IN COMBINATION 
WITH A FUSELAGE AT HIGH SUBSONIC MACH 
NUMBERS AND AT A MACH NUMBER OF 1.2. 
Arvo A. Luoma. June 6, 1951. 59p. diagrs., photo., 
tab. (NACA RM L51D13) 



TABULATED PRESSURE COEFFICIENTS AND 
AERODYNAMIC CHARACTERISTICS MEASURED 
ON THE WING OF THE BELL X-l AIRPLANE IN 
AN UNACCELERATED STALL AND IN PULL-UPS 
AT MACH NUMBERS OF 0.74, 0.75, 0.94, AND 
0.97. Lawrence A. Smith. June 19, 1951. 49p. 
diagrs., photo., tabs. (NACA RM L51B23) 



CHARACTERISTICS THROUGHOUT THE SUBSONIC 
SPEED RANGE OF A PLANE WING AND OF A 
CAMBERED AND TWISTED WING, BOTH HAVING 
45° OF SWEEPBACK. Ben H. Johnson, Jr., and 
Harry H. Shibata. July 1951. 122p. diagrs., 
photos. (NACA RM A51D27) 



INVESTIGATION OF THE EFFECTS OF TWIST AND 
CAMBER ON THE AERODYNAMIC CHARACTER- 
ISTICS OF A 50° 38' SWEPTBACK WING OF AS- 
PECT RATIO 2.98. TRANSONIC -BUMP METHOD. 

Kenneth P. Spreemann and William J. Alford, Jr. 
August 1951. 33p. diagrs., photos., tab. 
(NACA RML51C16) 



TRANSONIC -WING INVESTIGATION IN THE 
LANGLEY 8-FOOT HIGH-SPEED TUNNEL AT HIGH 
SUBSONIC MACH NUMBERS AND AT A MACH NUM- 
BER OF 1.2. ANALYSIS OF PRESSURE DISTRIBU- 
TION OF WING-FUSELAGE CONFIGURATION HAV- 
ING A WTNG OF 45° SWEEPBACK, ASPECT RATIO 
4, TAPER RATIO 0.6, AND NACA 65A006 AIRFOIL 
SECTION. Donald L. Loving and Bruce B. 
Estabrooks. September 1951. 132p. diagrs., photos. 
(NACARM L51F07) 



INVESTIGATION OF THE EFFECT OF A NACELLE 
AT VARIOUS CHORDWISE AND VERTICAL POSI- 
TIONS ON THE AERODYNAMIC CHARACTERISTICS 
AT HIGH SUBSONIC SPEEDS OF A 45° SWEPTBACK 
WING WITH AND WITHOUT A FUSELAGE. 
H. Norman Silvers, Thomas J. King, Jr., and 
Thomas B. Pasteur, Jr. September 1951. 71p. 
diagrs., photos., 3 tabs. (NACA RM L51H16) 



SOME EFFECTS OF FUSELAGE INTERFERENCE, 
WING INTERFERENCE AND SWEEPBACK ON THE 
DAMPING IN ROLL OF UNTAPEREi- -TNGS AS DE- 
TERMINED BY TECHNIQUES EMPLOYING 
ROCKET-PROPELLED VEHICLES. William M. 
Bland, Jr., and Albert E. Dietz. October 1951. 27p. 
diagrs., photos. (NACA RM L51D25) 



ROLLING EFFECTIVENESS OF ALL-MOVABLE 
WINGS AT SMALL ANGLES OF INCIDENCE AT 
MACH NUMBERS FROM 0.6 TO 1,6. H. Kurt 
Strass and Edward T. Marley. October 1951. 16p. 
diagrs., photo., tab. (NACA RM L51H03) 

DAMPING IN ROLL OF STRAIGHT AND 45° SWEPT 
WINGS OF VARIOUS TAPER RATIOS DETERMINED 
AT HIGH SUBSONIC, TRANSONIC, AND SUPER- 
SONIC SPEEDS WITH ROCKET-POWERED 
MODELS. E. Claude Sanders, Jr. October 1951. 
15p. diagrs. (NACA RM L51H14) 



WIND-TUNNEL INVESTIGATION OF THE AERODY- 
NAMIC CHARACTERISTICS IN PITCH OF WING- 
FUSELAGE COMBINATIONS AT HIGH SUBSONIC 
SPEEDS. ASPECT-RATIO SERIES. Richard E. 
Kuhn and James W. Wiggins. April 1952. 42p. 
diagrs., photos., tab. (NACA RM L52A29) 



TRANSONIC DRAG CHARACTERISTICS AND PRES- 
SURE DISTRIBUTION ON THE BODY OF A WING- 
BODY COMBINATION CONSISTING OF A BODY OF 
REVOLUTION OF FINENESS RATIO 12 AND A WING 
HAVING SWEEPBACK OF 45°, ASPECT RATIO 4, 
TAPER RATIO 0.6, AND NACA 65A006 AIRFOIL 
SECTIONS. Max C. Kurbjun and Jim Rogers 
Thompson. April 1952. 28p. diagrs., photo., tabs. 
(NACA RML52B12) 



THE EFFECTS OF REYNOLDS NUMBER AT MACH 
NUMBERS UP TO 0.94 ON THE LOADING ON A 35° 
SWEPTBACK WING HAVING NACA 65iA012 
STREAMWISE SECTIONS. Bruce E. Tinling and 
Armando E. Lopez. June 1952. 115p. diagrs., 
photos., tabs. (NACA RM A52B20) 



AN INVESTIGATION THROUGHOUT THE SUBSONIC 
SPEED RANGE OF A FULL-SPAN AND A SEMI- 
SPAN MODEL OF A PLANE WING AND OF A 
CAMBERED AND TWISTED WING, ALL HAVING 
45° OF SWEEPBACK. Harry H. Shibata, Angelo 
Bandettini, and Joseph Cleary. June 1952. 65p. 
diagrs., photos. (NACA RM A52D01) 

A STUDY OF THE FLOW OVER A 45° SWEPTBACK 
WING-FUSELAGE COMBINATION AT TRANSONIC 
MACH NUMBERS. Richard T. Whitcomb and 
Thomas C. Kelly. June 1952. 60p. diagrs., 
photos. (NACA RM L52D01) 

DAMPING IN ROLL OF MODELS WITH 45°, 60°, 
AND 70° DELTA WINGS DETERMINED AT HIGH 
SUBSONIC, TRANSONIC, AND SUPERSONIC 
SPEEDS WITH ROCKET-POWERED MODELS. 
E. Claude Sanders, Jr. June 1952. 18p. diagrs., 
photos, (NACA RM L52D22a) 



WIND-TUNNEL INVESTIGATION OF THE AERO- 
DYNAMIC CHARACTERISTICS IN PITCH OF WING- 
FUSELAGE COMBINATIONS AT HIGH -SUBSONIC 
SPEEDS. SWEEP SERIES. James W. Wiggins and 
Richard E. Kuhn. July 1952. 41p. diagrs., photos. 
(NACA RM L52D18) 



RESULTS OF TWO EXPERIMENTS ON FLUTTER 
OF HIGH-ASPECT-RATIO SWEPT WINGS IN THE 
TRANSONIC SPEED RANGE. W. T. Lauten, Jr., 
and Burke R. O'Kelly. July 1952. 22p. diagrs., 
photos., tabs. (NACA RM L52D24b) 

EFFECT OF FUSELAGE INTERFERENCE ON THE 
DAMPING IN ROLL OF DELTA WINGS OF ASPECT 
RATIO 4 IN THE MACH NUMBER RANGE BETWEEN 
0.6 AND 1.6 AS DETERMINED WITH ROCKET- 
PROPELLED VEHICLES. William M. Bland, Jr. 
July 1952. 13p. diagrs., photos. (NACA RM L52E13) 



EFFECT OF CAMBER AND TWIST ON THE STA- 
BILITY CHARACTERISTICS OF MODELS HAVING A 
45° SWEPT WING AS DETERMINED BY THE FREE- 
FALL METHOD AT TRANSONIC SPEEDS. Maurice 
D. White. August 1952. 35p. diagrs., photos., tab. 
(NACARMA52F16) 



44 



(1) AERODYNAMICS 



TRANSONIC FLIGHT TESTS TO DETERMINE THE 
EFFECT OF THICKNESS RATIO AND PLAN-FORM 
MODIFICATION ON THE ZERO-LIFT DRAG OF A 
45° SWEPTBACKWING. William B. Pepper, Jr., 
and Sherwood Hoffman. August 1952, 24p. diagrs., 
photos., tabs. (NACA RM L52F02a) 



FREE-FLIGHT TESTS AT MACH NUMBERS FROM 
0.8 TO 1.4 TO DETERMINE THE EFFECT ON 
ZERO-LIFT DRAG OF INCREASING THE LEADING- 
EDGE BLUNTNESS OF A 45° SWEPTBACK WING 
HAVING AN NACA 65A009 AIRFOIL. William B. 
Pepper, Jr. August 1952. 15p. diagrs., photos., 
tabs. (NACA RM L52F30) 



THE LONGITUDINAL CHARACTERISTICS AT MACH 
NUMBERS UP TO 0.92 OF A CAMBERED AND 
TWISTED WING HAVING 40° OF SWEEPBACK AND 
AN ASPECT RATIO OF 10. George G. Edwards, 
Bruce E. Tinling, and Arthur C. Ackerman. 
September 1952. 71p. diagrs., photos., tab. 
(NACA RM A52F18) 



A STUDY OF THE ZERO-LIFT DRAG-RISE CHAR- 
ACTERISTICS OF WING-BODY COMBINATIONS 
NEAR THE SPEED OF SOUND. Richard T 
Whitcomb. September 1952. 41p. diagrs., photos., 
3 tabs. (NACA RM L52H08) 



THE EFFECTS OF SWEEPBACK ON LONGITUDINAL 
CHARACTERISTICS OF A 1/30-SCALE SEMISPAN 
MODEL OF THE BELL X-5 AIRPLANE AS DETER- 
MINED FROM NACA WING-FLOW TESTS AT 
TRANSONIC SPEEDS. Joseph J, Kolnick and 
Robert M. Kennedy. November 1952. 48p. diagrs., 
photos., tab. (NACA RM L52I23) 

LOW-LIFT BUFFET CHARACTERISTICS OB- 
TAINED FROM FLIGHT TESTS OF UNSWEPT THIN 
INTERSECTING SURFACES AND OF THICK 35° 
SWEPTBACK SURFACES. Homer P. Mason. 
January 1953. 21p. diagrs., photos. (NACA 
RM L52H12) 

FREE-FLIGHT INVESTIGATION AT ZERO LIFT IN 
THE MACH NUMBER RANGE BETWEEN 0.7 AND 
1.4 TO DETERMINE THE EFFECTIVENESS OF AN 
INSET TAB AS A MEANS OF AERODYNAMIC ALLY 
RELIEVING AILERON HINGE MOMENTS. William 
M. Bland, Jr., and Edward T. Marley. January 
1953, I9p. diagrs., photos. {NACA RM L52K07) 

INVESTIGATION OF THE EFFECT OF CHORDWISE 
POSITIONING AND SHAPE OF AN UNDERWING NA- 
CELLE ON THE HIGH-SPEED AERODYNAMIC 
CHARACTERISTICS OF A 45° SWEPTBACK 
TAPERED-IN-THICKNESS-RATIO WING OF AS- 
PECT RATIO 6. H. Norman Silvers and Thomas J. 
King, Jr. January 1953. 50p. diagrs. 
(NACA RM L52K25) 

FLIGHT MEASUREMENTS O* THE STABILITY 
CHARACTERISTICS OF THE BELL X-5 RESEARCH 
AIRPLANE IN SIDESLIPS AT 59° SWEEPBACK. 
JoanM. Childs. February 1953. 23p. diagrs., 
photos., tab. (NACA RM L52K13b) 

WIND-TUNNEL INVESTIGATION OF THE STATIC 
LATERAL STABILITY CHARACTERISTICS OF 
WING-FUSELAGE COMBINATIONS AT HIGH SUB- 
SONIC SPEEDS. ASPECT-RATIO SERIES. Paul G. 
Fournier and Andrew L. Byrnes, Jr. February 1953. 
26p. diagrs., photos. (NACA RM L52L18) 



PRESSURE DISTRIBUTION AT MACH NUMBERS UP 
TO 0.90 ON A CAMBERED AND TWISTED WING 
HAVING 40° OF SWEEPBACK AND AN ASPECT 
RATIO OF 10, INCLUDING THE EFFECTS OF 
FENCES. Frederick W. Boltz and Harry H. 
Shibata. March 1953. 133p. diagrs., photos., tabs. 
(NACA RM A52K20) 

WIND-TUNNEL INVESTIGATION OF STALL CON- 
TROL BY SUCTION THROUGH A POROUS LEADING 
EDGE ON A 37° SWEPTBACK WING OF ASPECT 
RATIO 6 AT REYNOLDS NUMBERS FROM 2.50 x 10 6 
to 8.10 x 10 6 . Robert R. Graham and William A. 
Jacques. March 1953. 67p. diagrs., photo., 2 tabB. 
(NACARML52L05) 

INVESTIGATION OF THE DAMPING IN ROLL OF 
SWEPT AND TAPERED WINGS AT SUPERSONIC 
SPEEDS. Russell W. McDearmon and Harry S. 
Heinke, Jr. March 1953. 35p. diagrs., photos., 
tab. (NACA RM L53A13) 



EXPERIMENTAL INVESTIGATION OF THE EF- 
FECTS OF PLAN-FORM TAPER ON THE AERO- 
DYNAMIC CHARACTERISTICS OF SYMMETRICAL 
UNSWEPT WINGS OF VARYING ASPECT RATIO. 

Edwin C. Allen. May 1953. 53p. diagrs., photos., 
tab. (NACA RM A53C19) 

THE EFFECT AT HIGH SUBSONIC SPEEDS OF A 
FLAP-TYPE AILERON ON THE CHORDWISE PRES- 
SURE DISTRIBUTION NEAR MIDSEMISPAN OF A 
TAPERED 35° SWEPTBACK WING OF ASPECT 
RATIO 4 HAVING NACA 65A006 AIRFOIL SECTION. 
Alexander D. Hammond and Barbara M. Keffer. 
May 1953. 89p. diagrs., tab. (NACA RM L53C23) 

FREE-FALL MEASUREMENTS OF THE EFFECTS 
OF WING -BODY INTERFERENCE ON THE TRAN- 
SONIC DRAG CHARACTERISTICS OF SWEPT -WING- 
SLENDER-BODY CONFIGURATIONS. Max C. 
Kurbjun and Jim Rogers Thompson. May 1953. 34p. 
diagrs., photos., tabs. (NACA RM L53C31) 



EFFECTS OF HORIZONTAL-TAIL HEIGHT AND A 
WING LEADING-EDGE MODIFICATION CON- 
SISTING OF A FULL-SPAN FLAP AND A PARTIAL- 
SPAN CHORD-EXTENSION ON THE AERODYNAMIC 
CHARACTERISTICS IN PITCH AT HIGH SUBSONIC 
SPEEDS OF A MODEL WITH A 45° SWEPTBACK 
WING. William D. Morrison, Jr. and William J. 
Alford, Jr. June 1953. 37p. diagrs., photo., tab. 
fNACA RM L53E06) 

WIND-TUNNEL INVESTIGATION OF THE AERODY- 
NAMIC CHARACTERISTICS IN PITCH OF WING- 
FUSELAGE COMBINATIONS AT HIGH SUBSONIC 
SPEEDS. TAPER- RATIO SERIES. Thomas J. 
King, Jr. and Thomas B. Pasteur, Jr. June 1953. 
37p. diagrs., photos., tab. (NACA RM L53E20) 



COMPARISON OF LIFT-CURVE SLOPES FOR A 
MODEL TESTED IN TWO SLOTTED TUNNELS OF 
DIFFERENT SIZES AT HIGH SUBSONIC SPEEDS. 
Robert W. Boswinkle, Jr. June 1953. 13p. 
diagrs. (NACA RM L53E20a) 

A COLLECTION OF DATA FOR ZERO-LIFT DAMP- 
ING IN ROLL OF WING-BODY COMBINATIONS AS 
DETERMINED WITH ROCKET-POWERED MODELS 
EQUIPPED WITH ROLL-TORQUE NOZZLES. 

David G. Stone. July 1953. 23p. diagrs., tab. 
(NACA RM L53E26) 



45 



(1) AERODYNAMICS 



WIND-TUNNEL INVESTIGATION OF THE EFFECTS 
OF GEOMETRIC DIHEDRAL ON THE AERODYNAM- 
IC CHARACTERISTICS IN PITCH AND SIDESLIP OF 
AN UNSWEPT- AND A 45° SWEPTBACK-WING 
FUSELAGE COMBINATION AT HIGH SUBSONIC 
SPEEDS. Richard E. Kuhn andJohn W. Draper. 
July 1953. 41p. diagrs., photos. 
(NACA RM L53F091 



THE EFFECTS OF LEADING-EDGE EXTENSIONS, 
A TRAILING- EDGE EXTENSION, AND A FENCE 
ON THE STATIC LONGITUDINAL STABILITY OF A 
WING-FUSELAGE-TAIL COMBINATION HAVING 
A WING WITH 350 OF SWEEPBACK AND AN AS- 
PECT RATIO OF 4.5. Ralph Selan and Angelo 
Bandettini. August 1953. 81p. diagrs,, photos., 
tabs. (NACA RM A53E12) 



THE LATERAL CONTROL CHARACTERISTICS OF 
CONSTANT-PERCENT-CHORD TRAILING-EDGE 
ELEVONS ON A POINTED WING OF ASPECT RATIO 
2 AT MACH NUMBERS UP TO 0.95. Verlln D. Reed 
and Donald W, Smith. August 1953. 105p. diagrs,, 
photo., tabs. (NACA RM A53F03) 



THE EFFECTS OF FENCES ON THE HIGH-SPEED 
LONGITUDINAL STABILITY OF A SWEPT-WING 
AIRPLANE. Richard S, Bray. August 1953. 37p. 
diagrs., photos., tabs. (NACA RM A53F23) 



EFFECT OF REDUCTION IN THICKNESS FROM 6 
TO 2 PERCENT AND REMOVAL OF THE POINTED 
TIPS ON THE SUBSONIC STATIC LONGITUDINAL 
STABILITY CHARACTERISTICS OF A 60° TRIANGU- 
LAR WING IN COMBINATION WITH A FUSELAGE. 
William E. Palmer. August 1953. 44p. diagrs., 
photo., tab. (NACA RM L53F24) 



THEORY OF WING-BODY DRAG AT SUPERSONIC 
SPEEDS. Robert T. Jones. September 1953. lip. 
diagrs. (NACA RM A53H18a) 



FLIGHT MEASUREMENTS OF LIFT AND DRAG 
FOR THE BELL X-l RESEARCH AIRPLANE HAV- 
ING A 10-PERCENT-THICK WING. Edwin J. 
Saltzman. September 1953. 37p. diagrs., tab 
(NACA RM L53F08) 



A TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE LONGITUDINAL STABILITY AND CONTROL 
CHARACTERISTICS OF A 0.09-SCALE MODEL OF 
THE BELL X-5 RESEARCH AIRPLANE AND COM- 
PARISON WITH FLIGHT. Ralph P. Bielat and 
George S. Campbell. October 1953. 65p. diagrs., 
photo. (NACA RM L53H18) 



SOME EFFECTS OF AEROELASTICITY AND 
SWEEPBACK ON THE ROLLING EFFECTIVENESS 
AND DRAG OF A 1/11-SCALE MODEL OF THE 
BELL X-5 AIRPLANE WING AT MACH NUMBERS 
FROM 0.6 TO 1.5. Roland D. English. November 
1953. 21p. diagrs., photos. (NACA RM L53I18b) 



WIND-TUNNEL INVESTIGATION OF THE EFFECTS 
OF STEADY ROLLING ON THE AERODYNAMIC 
LOADING CHARACTERISTICS OF A 45° SWEPT - 
BACK WING AT HIGH SUBSONIC SPEEDS. James 
W. Wiggins and Richard E. Kuhn. November 1953. 
22p. diagrs., photos. (NACA RM L53J01a) 



DOWNWASH BEHIND A TRIANGULAR WING OF 
ASPECT RATIO 3 - TRANSONIC BUMP METHOD. 
John A. Axelson. December 1953. 37p. diagrs., 
photo., tab. (NACA RM A53I23) 

AN EXPERIMENTAL AND THEORETICAL INVES- 
TIGATION AT HIGH SUBSONIC SPEEDS OF THE 
EFFECTS OF HORIZONTAL-TAIL HEIGHT ON THE 
AERODYNAMIC CHARACTERISTICS IN SIDESLIP 
OF AN UNSWEPT, UNTAPERED TAIL ASSEMBLY. 
Harleth G. Wiley and Donald R. Riley. December 
1953. 71p. diagrs., tab. (NACA RM L53J19) 



WIND-TUNNEL INVESTIGATION AT HIGH AND LOW 
SUBSONIC MACH NUMBERS OF TWO UNSWEPT 
WINGS HAVING NACA 2-006 AND NACA 65A006 
AIRFOIL SECTIONS. Stanley F. Racisz. 
December 1953. 40p. diagrs., photo., tab. 
(NACA RM L53J29) 

THE EFFECTS OF HORIZONTAL-TAIL HEIGHT 
AND A PARTIAL-SPAN LEADING-EDGE EXTEN- 
SION ON THE STATIC LONGITUDINAL STABILITY 
OF A WING- FUSELAGE -TAIL COMBINATION 
HAVING A SWEPTBACK WING. Angelo Bandettini 
and Ralph Selan. March 1954. 54p. diagrs., 
photos., 2 tabs. (NACA RM A53J07) 



THE TRANSONIC CHARACTERISTICS OF UNSWEPT 
WINGS HAVING ASPECT RATIOS OF 4, SPANWISE 
VARIATIONS IN THICKNESS RATIO, AND VARIA- 
TIONS IN PLAN-FORM TAPER - TRANSONIC- 
BUMP TECHNIQUE. Warren H. Nelson. March 
1954. 29p. diagrs., photo. (NACA RM A53L17) 



CHORDWISE PRESSURES AND SECTION FORCE 
AND MOMENT COEFFICIENTS AT HIGH SUBSONIC 
SPEEDS NEAR MIDSPAN OF A TAPERED 35° 
SWEPTBACK WING WITH A FLAP-TYPE CONTROL 
AND AN ATTACHED TAB. Alexander D. Hammond 
and Barbara M. Keffer. March 1954. 57p. diagrs., 
35 tabs. (NACA RM L54A22) 



HINGE-MOMENT, LIFT, AND P1TCHING-MOMENT 
CHARACTERISTICS OF A FLAP-TYPE CONTROL 
SURFACE HAVING VARIOUS HINGE-LINE LOCA- 
TIONS ON A 4-PERCENT-THICK 60° DELTA WING. 
TRANSONIC -BUMP METHOD. Robert F, Thompson. 
March 1954. 73p. diagrs., photo. 
fNACA RM L54B08) 



EFFECTS OF OPERATING PROPELLERS ON THE 
WING-SURFACE PRESSURES OF A FOUR-ENGINE 
TRACTOR AIRPLANE CONFIGURATION HAVING A 
WING WITH 40° OF SWEEPBACK. Carl D. Kolbe 
and Frederick W, Boltz. April 1954. 133p. 
diagrs., photo., 19 tabs. (NACA RM A53L29) 



THE TRANSONIC AERODYNAMIC CHARACTER- 
ISTICS OF STRUCTURALLY RELATED WINGS OF 
LOW ASPECT RATIO HAVING A SPANWISE VARIA- 
TION IN THICKNESS RATIO - TRANSONIC BUMP 
TECHNIQUE. Joseph W. Cleary. April 1954. 
28p. diagrs., photo. (NACA RM A54B18) 



FLIGHT INVESTIGATION OF THE EFFECTS OF A 
PARTIAL-SPAN LEADING-EDGE CHORD EXTEN- 
SION OF THE AERODYNAMIC CHARACTERISTICS 
OF A 35° SWEPT-WING FIGHTER AIRPLANE. 
Frederick H. Matteson and Rudolph D. Van Dyke, Jr. 
April 1954. 34p. diagrs., photos., tabs. 
(NACA RM A54B26) 



46 



(1) AERODYNAMICS 



EFFECTS OF SWEEP AND THICKNESS ON THE 
STATIC LONGITUDINAL AERODYNAMIC CHARAC- 
TERISTICS OF A SERIES OF THIN, LOW-ASPECT- 
RATIO, HIGHLY TAPERED WINGS AT TRANSONIC 
SPEEDS. TRANSONIC-BUMP METHOD. Albert G. 
Few, Jr., and Paul G. Fournier, April 1954. 107p. 
diagrs., photo., tab. (NACA RM L54B25) 



THE EFFECT OF BLUNT-TRAILING-EDGE MODI- 
FICATIONS ON THE HIGH-SPEED STABILITY AND 
CONTROL CHARACTERISTICS OF A SWEPT -WING 
FIGHTER AIRPLANE. Melvin Sadoff, Frederick H. 
Matteson, and Rudolph D. Van Dyke, Jr. May 1954. 
55p. diagrs., photos., tab. (NACA RM A54C31) 



FLIGHT DETERMINATION OF THE BUFFETING 
CHARACTERISTICS OF THE BELL X-5 RESEARCH 
AIRPLANE AT 58.7° SWEEPBACK. Donald W. 
Briggs. May 1954. 31p. diagrs., photo., tabs. 
(NACARM L54C17) 



EFFECT AT TRANSONIC SPEEDS OF INBOARD 
SPOILERS ON THE STATIC LONGITUDINAL STA- 
BILITY CHARACTERISTICS OF A 45° SWEPTBACK 
WING-BODY COMBINATION HAVING A LEADING- 
EDGE CHORD -EXTENSION. James H. Henderson. 
June 1954. 24p. diagrs., photo. 
(NACA RML54D13) 



COMPARISON BETWEEN THEORETICAL AND EX- 
PERIMENTAL RATES OF ROLL OF TWO MODELS 
WITH FLEXIBLE RECTANGULAR WINGS AT SU- 
PERSONIC SPEEDS. John M. Hedgepeth and 
Robert J. Kell. August 1954. 21p. diagrs., photo., 
tabs. (NACA RM L54F23) 



STATIC LONGITUDINAL STABILITY CHARACTER- 
ISTICS OF A COMPOSITE-PLAN-FORM WING 
MODEL INCLUDING SOME COMPARISONS WITH A 
45° SWEPTBACK WING AT TRANSONIC SPEEDS. 
Walter D. Wolhart. August 1954. 36p. diagrs., 
photo., tabs. (NACA RM L54F24) 



SOME EFFECTS OF EXTERNAL WING TIP STORES 
ON THE ROLLING EFFECTIVENESS AND DRAG OF 
PLAIN AND HALF-DELTA TIP AILERONS ON A 
4-PERCENT-THICK, TAPERED, UNSWEPT WING. 
Roland D. English. August 1954. l4p. diagrs., 
photos., tab. (NACA RM L54F29a) 



MEASUREMENT AND ANALYSIS OF WING AND 
TAIL BUFFETING LOADS ON A FIGHTER AIR- 
PLANE. Wilber B. Huston and T. H. Skopinski. 
1955. i, 27p. diagrs., photo., tabs. (NACA Rept. 
1219. Supersedes TN 3080) 



A METHOD FOR THE DESIGN OF SWEPTBACK 
WINGS WARPED TO PRODUCE SPECIFIED FLIGHT 
CHARACTERISTICS AT SUPERSONIC SPEEDS. 
Warren A Tucker. 1955. i. 17p. diagrs., tabs. 
(NACA Rept. 1226. Supersedes RM L51 F08) 

AN INVESTIGATION OF THE MAXIMUM LIFT OF 
WINGS AT SUPERSONIC SPEEDS. James J. 
Gallagher and James N. Mueller. 1955. ii, 28p. 
diagrs., photos., tabs. (NACA Rept. 1227. Super- 
sedes RM L7J10) 



A FLIGHT EVALUATION OF THE LONGITUDINAL 
STABILITY CHARACTERISTICS ASSOCIATED WITH 
THE PITCH-UP OF A SWEPT -WING AIRPLANE IN 
MANEUVERING FLIGHT AT TRANSONIC SPEEDS. 
SethB. Anderson and Richard S. Bray. 1955. ii, 
12p. diagrs., photo., tab. (NACA Rept. 1237. 
Supersedes RM A51I12) 

INVESTIGATIONS AT SUPERSONIC SPEEDS OF 22 
TRIANGULAR WINGS REPRESENTING TWO AIR- 
FOIL SECTIONS FOR EACH OF 11 APEX ANGLES. 
Eugene S. Love. 1955. il, 60p. diagrs., photos., 
tabs. (NACA Rept. 1238. Supersedes RM L9D07) 

A CORRELATION BY MEANS OF TRANSONIC 
SIMILARITY RULES OF EXPERIMENTALLY DE- 
TERMINED CHARACTERISTICS OF A SERIES OF 
SYMMETRICAL AND CAMBERED WINGS OF 
RECTANGULAR PLAN FORM. John B. McDevitt. 
1955. ii, 23p. diagrs., tabs. (NACA Rept. 1253. 
Supersedes RM A51L17b; RM A53G31) 



A COMPARISON OF TWO METHODS FOR COMPUT- 
ING THE WAVE DRAG OF WING-BODY COMBINA- 
TIONS. Alberta Alksne. April 1955. 32p. diagrs. 
(NACA RM A55A06a) 

WING-LOAD MEASUREMENTS OF THE BELL X-5 
RESEARCH AIRPLANE AT A SWEEP ANGLE OF 
58.7°. Richard D. Banner, Robert D. Reed, and 
William L. Marcy. April 1955. 22p. diagrs., 
photo., tab. (NACA RM H55A11) 

THE TRANSONIC CHARACTERISTICS OF 22 
RECTANGULAR, SYMMETRICAL WING MODELS 
OF VARYING ASPECT RATIO AND THICKNESS. 

Warren H. Nelson and John B. McDevitt. June 1955. 
109p. diagrs., photos. (NACA TN 3501. Formerly 
RM A51A12) 

THE TRANSONIC CHARACTERISTICS OF 38 
CAMBERED RECTANGULAR WINGS OF VARYING 
ASPECT RATIO AND THICKNESS AS DETERMINED 
BY THE TRANSONIC -BUMP TECHNIQUE. Warren 
H. Nelson and Walter J. Krumm. June 1955. 173p. 
diagrs., photos. (NACA TN 3502. Formerly 
RM A52D11) 

EFFECTS OF SWEEP ON THE MAXIMUM -LIFT 
CHARACTERISTICS OF FOUR ASPECT-RATIO-4 
WINGS AT TRANSONIC SPEEDS. Thomas R. Turner. 
July 1955. 25p. diagrs. (NACA TN 3468. Formerly 
RM L50H11) 



SUMMARY OF RESULTS OF A WIND-TUNNEL 
INVESTIGATION OF NINE RELATED HORIZONTAL 
TAILS. Jules B. Dods, Jr. and Bruce E. f inling. 
July 1955. 105p. diagrs., 2 tabs. (NACA TN 3497. 
Formerly RM A51G31a) 

ANALYSIS OF 1HE HORIZONTAL-TAIL LOADS 
MEASURED IN FLIGHT ON A MULTIENGINE JET 
BOMBER. William S. Aiken, Jr. and Bernard 
Wiener. September 1955. i, 69p. diagrs., photo., 
6 tabs. (NACA TN 3479) 

MEASUREMENTS OF THE EFFECTS OF FINITE 
SPAN ON THE PRESSURE DISTRIBUTION OVER 
DOUBLE-WEDGE WINGS AT MACH NUMBERS 
NEAR SHOCK ATTACHMENT. Walter G. Vincenti. 
September 1955. 50p. diagrs. (NACA TN 3522) 



47 



(1) AERODYNAMICS 



THE EFFECTIVENESS OF WING VORTEX GENERA- 
TORS IN IMPROVING THE MANEUVERING CHARAC- 
TERISTICS OF A SWEPT-WING AIRPLANE AT 
TRANSONIC SPEEDS. Norman M. McFadden, 
George A. Rathert, Jr., and Richard S. Bray. 
September 1955. 43p. diagrs. , photos., tab. 
(NACA TN 3523. Supersedes RM A51J18) 



SUMMARY OF RESULTS OBTAINED BY 
TRANSONIC -BUMP METHOD ON EFFECTS OF 
PLAN FORM AND THICKNESS ON LIFT AND DRAG 
CHARACTERISTICS OF WINGS AT TRANSONIC 
SPEEDS, Edward C. Polhamus. November 1955. 
33p. diagrs., tab. (NACA TN 3469. Supersedes 
RM L51H30) 



FLIGHT INVESTIGATION AT MACH NUMBERS 
FROM 0.6 TO 1.7 TO DETERMINE DRAG AND 
BASE PRESSURES ON A BLUNT-TRAILTNG-EDGE 
AIRFOIL AND DRAG OF DIAMOND AND CIRCULAR- 
ARC AIRFOILS AT ZERO LIFT. John D. Morrow 
and Ellis Katz. November 1955. 19p. diagrs., 
photos. (NACA TN 3548. Supersedes RM L50E19a) 



MEASUREMENTS OF THE EFFECT OF TRAILING- 
EDGE THICKNESS ON THE ZERO- LIFT DRAG OF 
THIN LOW- ASPECT -RATIO WINGS. John D. 
Morrow. November 1955. lip. diagrs., photo. 
(NACA TN 3550. Supersedes RM L50F26) 



THE TRANSONIC CHARACTERISTICS OF 36 SYM- 
METRICAL WINGS OF VARYING TAPER, ASPECT 
RATIO, AND THICKNESS AS DETERMINED BY THE 
TRANSONIC -BUMP TECHNIQUE. Warren H. 
Nelson, Edwin C. Allen, and Walter J. Krumm. 
December 1955. 131p. diagrs., photo. 
(NACA TN 3529. Supersedes RM A53I29> 



PRELIMINARY STUDY OF SOME FACTORS WHICH 
AFFECT THE STALL-FLUTTER CHARACTER- 
ISTICS OF THIN WINGS. A. Gerald Rainey. March 
1956. 33p. diagrs., photo., tab. (NACA TN 3622. 
Supersedes RM L52D08) 



AN ANALYSIS OF ESTIMATED AND EXPERI- 
MENTAL TRANSONIC DOWNWASH CHARACTER- 
ISTICS AS AFFECTED BY PLAN FORM AND THICK- 
NESS FOR WING AND WING- FUSELAGE CONFIG- 
URATIONS. Joseph Weil, George S. Campbell and 
Margaret S. Diederlch. April 1956. 92p. diagrs., 
photos., tabs. (NACA TN 3628. Supersedes 
RM L52I22) 



INVESTIGATION AT HIGH SUBSONIC SPEEDS OF A 
BODY- CONTOURING METHOD FOR ALLEVIATING 
THE ADVERSE INTERFERENCE AT THE ROOT OF 
A SWEPTBACK WING. John B. McDevitt and 
William M. Haire. April 1956. 38p. diagrs., 
photos. (NACA TN 3672. Supersedes RM A54A22) 



WIND-TUNNEL INVESTIGATION OF THE EFFECT 
OF CLIPPING THE TIPS OF TRIANGULAR WINGS 
OF DIFFERENT THICKNESS, CAMBER, AND AS- 
PECT RATIO - TRANSONIC BUMP METHOD 
Horace F. Emerson. June 1956. 183p. diagrs., 
photo,, tabs. (NACA TN 3671. Supersedes 
RM A53L03) 



FLIGHT TESTS AT SUPERSONIC SPEEDS TO 
DETERMINE THE EFFECT OF TAPER ON THE 
ZERO-LIFT DRAG OF SWEPTBACK LOW-ASPECT- 
RATIO WINGS. Murray Pittel. June 1956. 20p. 
diagrs., photos. (NACA TN 3697. Supersedes 
RM L50F30a) 

THE FLOW PAST AN UNSWEPT- AND A SWEPT- 
WING— BODY COMBINATION AND THEIR EQUP7A- 
LENT B0DD3S OF REVOLUTION AT MACH NUM- 
BERS NEAR 1.0. Walter F. Lindsey. June 1956. 
18p. diagrs., photos. (NACA TN 3703. Supersedes 
RM L54A28a) 



PRELIMINARY WIND-TUNNEL TESTS OF TRIAN- 
GULAR AND RECTANGULAR WINGS IN STEADY 
ROLL AT MACH NUMBERS OF 1.62 AND 1.92. 
Clinton E. Brown and Harry S. Heinke, Jr. 
June 1956. 36p. diagrs., tabs. 
(NACA TN 3740. Supersedes RM L8L30) 



(1. 2.2.7) 

WAKE 



LONGITUDINAL STABILITY CHARACTERISTICS OF 
A 42° SWEPTBACK WING AND TAIL COMBINATION 
AT A REYNOLDS NUMBER OF 6.8 x 10 6 . Stanley H. 
Spooner and Albert P. Martina. July 22, 1948. 
44p. diagrs., photos., 2 tabs. (NACA RM L8E12) 



EFFECTS OF HIGH-LIFT AND STALL-CONTROL 
DEVICES, FUSELAGE, AND HORIZONTAL TAIL ON 
A WING SWEPT BACK 42° AT THE LEADING EDGE 
AND HAVING SYMMETRICAL CIRCULAR-ARC AIR- 
FOIL SECTIONS AT A REYNOLDS NUMBER OF 
6.9 x 10 6 . Robert L. Woods and Stanley H. 
Spooner. April 20, 1949. 42p. diagrs., photos., 
tabs, {NACA RM L9B11) 



A STUDY OF SEVERAL FACTORS AFFECTING THE 
STABILITY CONTRIBUTED BY A HORIZONTAL 
TAIL AT VARIOUS VERTICAL POSITIONS ON A 
SWEPTBACK-WING AIRPLANE MODEL. Gerald V. 
Foster and Roland F. Griner. October 28, 1949. 
28p. diagrs., tab. (NACA RM L9H19) 



INVESTIGATION OF DOWNWASH AND WAKE 
CHARACTERISTICS AT A MACH NUMBER OF 1.53. 
IH - SWEPT WINGS. Edward W. Perkins and 
Thomas N. Canning. February 23, 1950. 41p. 
diagrs., tab. (NACA RM A9K02) 



A TRANSONIC -WING INVESTIGATION IN THE 
LANGLEY 8-FOOT HIGH-SPEED TUNNEL AT HIGH 
SUBSONIC MACH NUMBERS AND AT A MACH 
NUMBER OF 1.2. WING-FUSELAGE CONFIGURA- 
TION WITH A WING OF 45° SWEEPBACK, ASPECT 
RATIO 4, TAPER RATIO 0.6, AND NACA 65A006 
AIRFOIL SECTION. Robert S. Osborne. 
October 10, 1950. 49p. diagrs., photos. 
(NACA RM L50H08) 



48 



(1) AERODYNAMICS 



A TRANSONIC WING INVESTIGATION IN THE 
LANGLEY 8- FOOT HIGH-SPEED TUNNEL AT HIGH 
SUBSONIC MACH NUMBERS AND AT A MACH 
NUMBER OF 1.2. WING-FUSELAGE CONFIGURA- 
TION HAVING A WING OF 35° SWEEPBACK, AS- 
PECT RATIO 4, TAPER RATIO 0.6, AND NACA 
65A006 AIRFOIL SECTION. Beverly Z. Henry, Jr. 
November 15, 1950. 40p. diagrs., photo., tab. 
(NACA RM L50J09) 



HOPIZONTAL-TAIL EFFECTIVENESS AND DOWN- 
WAS fi SURVEYS FOR TWO 47.7° SWEPTBACK 
WING-FUSELAGE COMBINATIONS WITH ASPECT 
RATIOS OF 5.1 AND 6.0 AT A REYNOLDS NUMBER 
OF 6.0 x 10 6 . Reino J. Salmi. January 12, 1951. 
65p. diagrs., photos., 2 tabs. (NACA RM L50K06) 



A TRANSONIC -WING INVESTIGATION IN THE 
LANGLEY 8-FOOT HIGH-SPEED TUNNEL AT HIGH 
SUBSONIC MACH NUMBERS AND AT A MACH NUM- 
BER OF 1.2. WING-FUSELAGE CONFIGURATION 
HAVING A WING OF 60° SWEEPBACK, ASPECT 
RATIO 4, TAPER RATIO 0.6, AND NACA 65A006 
AIRFOIL SECTION. Raymond B. Wood and Frank F. 
Fleming. January 24, 1951. 43p. diagrs., photo. 
(NACA RM L50J25) 



AERODYNAMIC CHARACTERISTICS INCLUDING 
PRESSURE DISTRIBUTIONS OF A FUSELAGE AND 
THREE COMBINATIONS OF THE FUSELAGE WITH 
SWEPT-BACK WINGS AT HIGH SUBSONIC SPEEDS. 
Fred B. Sutton and Andrew Martin. February 6, 
1951. 117p. diagrs., photos., tabs. 
(NACA RM A50J26a) 



LOW-SPEED LONGITUDINAL AND WAKE AIR- 
FLOW CHARACTERISTICS AT A REYNOLDS NUM- 
BER OF 6.0 x 10 6 OF A 52° SWEPTBACK WING 
EQUIPPED WITH VARIOUS SPANS OF LEADING- 
EDGE AND TRAILING-EDGE FLAPS, A FUSELAGE, 
AND A HORIZONTAL TAIL AT VARIOUS VERTICAL 
POSITIONS. Roland F. Griner and Gerald V. Foster. 
February 28, 1951. 66p. diagrs., photo., 3 tabs. 
(NACA RM L50K29) 



A TRANSONIC -WING INVESTIGATION IN THE 
LANGLEY 8-FOOT HIGH-SPEED TUNNEL AT 
HIGH SUBSONIC MACH NUMBERS AND AT A 
MACH NUMBER OF 1.2. WING-FUSELAGE CON- 
FIGURATION HAVING A WING OF 0° SWEEPBACK, 
ASPECT RATIO 4.0, TAPER RATIO 0.6, AND NACA 
65A006 AIRFOIL SECTION. Maurice S. Cahn and 
Carroll R. Bryan. March 6, 1951. 37p. diagrs., 
photos. (NACA RM L51A02) 



TESTS IN THE AMES 40- BY 80-FOOT WIND TUN- 
NEL OF AN AIRPLANE CONFIGURATION WITH AN 
ASPECT RATIO 2 TRIANGULAR WING AND AN 
ALL-MOVABLE HORIZONTAL TAIL- 
LONGITUDINAL CHARACTERISTICS. David Graham 
and David G. Koenig. April 23, 1951. 35p. diagrs., 
photo., 3 tabs. (NACA RM A51B21) 



AERODYNAMIC CHARACTERISTICS OF FOUR 
WINGS OF SWEEPBACK ANGLES 0°, 35°, 45°, AND 
60° NACA 65A006 AIRFOIL SECTION, ASPECT 
RATIO 4, AND TAPER RATIO 0.6 IN COMBINATION 
WITH A FUSELAGE AT HIGH SUBSONIC MACH 
NUMBERS AND AT A MACH NUMBER OF 1.2. 
Arvo A. Luoma. June 6, 1951. 59p. diagrs., photo., 
tab. (NACA RM L51D13) 



LOW -SPEED LONGITUDINAL AND WAKE AIR- 
FLOW CHARACTERISTICS AT A REYNOLDS NUM- 
BER OF 5.5 x 10 6 OF A CIRCULAR-ARC 52° 
SWEPTBACK WING WITH A FUSELAGE AND A 
HORIZONTAL TAIL AT VARIOUS VERTICAL POSI- 
TIONS. Gerald V. Foster and Roland F. Griner. 
June 19, 1951. 44p. diagrs., tabs. 
(NACA RM L51C30) 

TESTS IN THE AMES 40- BY 80-FOOT WIND TUN- 
NEL OF AN AIRPLANE CONFIGURATION WITH AN 
ASPECT RATIO 4 TRIANGULAR WING AND AN 
ALL-MOVABLE HORIZONTAL TAIL - LONGITUDI- 
NAL CHARACTERISTICS. David Graham and 
David G. Koenig. October 1951. 27p. diagrs., 
photo., 4 tabs. (NACA RM A51H10a) 

DOWNWASH AND SIDEWASH FIELDS BEHIND 
CRUCIFORM WINGS. John R. Spreiter. January 
1952. 18p. photos., diagrs. (NACA RM A51L17) 

INVESTIGATION OF THE LOW-SPEED AERO- 
DYNAMIC CHARACTERISTICS OF A VARIABLE - 
SWEEP AIRPLANE MODEL WITH A WING HAVING 
PARTIAL-SPAN CAMBERED- LEADING- EDGE 
MODIFICATIONS. Robert E. Becht and Andrew L. 
Byrnes, Jr. September 1952. 47p. diagrs., photos. 
(NACA RM L52G08a) 



TESTS IN THE AMES 40- BY 80-FOOT WIND TUN- 
NEL OF AN AIRPLANE CONFIGURATION WITH AN 
ASPECT RATIO 3 TRIANGULAR WING AND AN 
ALL-MOVABLE HORIZONTAL TAIL - LONGITU- 
DINAL AND LATERAL CHARACTERISTICS. David 
G. Koenig. April 1953. 61p. diagrs., photos., 
4 tabs. (NACA RM A52L15) 

INVESTIGATION OF THE EFFECTS OF WING AND 
TAIL MODIFICATIONS ON THE LOW-SPEED STA- 
BILITY CHARACTERISTICS OF A MODEL HAVING 
A THIN 40° SWEPT WING OF ASPECT RATIO 3.5. 
Joseph Weil, William C. Sleeman, Jr., and Andrew 
L. Byrnes, Jr. April 1953. 95p. diagrs., photos., 
tab. (NACA RM L53C09) 

LONGITUDINAL STABILITY AND WAKE-FLOW 
CHARACTERISTICS OF A TWISTED AND 
CAMBERED WING-FUSELAGE COMBINATION OF 
45° SWEEPBACK AND ASPECT RATIO 8 WITH A 
HORIZONTAL TAIL AND STALL-CONTROL DE- 
VICES AT A REYNOLDS NUMBER OF 4.0 x 10 6 . 
Gerald V. Foster. June 1953. 51p. diagrs., 
photos., tab. (NACA RM L53D08) 



DOWNWASH BEHIND A TRIANGULAR WING OF 
ASPECT RATIO 3 - TRANSONIC BUMP METHOD. 
John A. Axelson. December 1953. 37p. diagrs., 
photo., tab. (NACA RM A53I23) 



THE NORMAL COMPONENT OF THE INDUCED 
VELOCITY IN THE VICINITY OF A LIFTING ROTOR 
AND SOME EXAMPLES OF ITS APPLICATION. 

Walter Castles, Jr. and Jacob Henri De Leeuw, 
Georgia Institute of Technology. 1954. ii, 15p. 
diagrs., 3 tabs. (NACA Rept. 1184. Formerly 
TN 2912) 



AN ANALYTICAL STUDY OF THE EFFECT OF 
AIRPLANE WAKE ON THE LATERAL DISPERSION 
OF AERIAL SPRAYS. Wilmer H. Reed, HI. 1954. 
ii, 16p. diagrs., 3 tabs. (NACA Rept. 1196. 
Formerly TN 3032) 



49 



(1 ) AERODYNAMICS 



THE EFFECTS OF HORIZONTAL-TAIL HEIGHT 
AND A PARTIAL-SPAN LEADING-EDGE EXTEN- 
SION ON THE STATIC LONGITUDINAL STABILITY 
OF A WING-FUSELAGE-TAIL COMBINATION 
HAVING A SWEPTBACK WING. Angelo Bandettini 
and Ralph Selan. March 1954. 54p. diagrs., 
photos., 2 tabs. (NACA RM A53J07) 

EFFECT OF GROUND INTERFERENCE ON THE 
AERODYNAMIC AND FLOW CHARACTERISTICS OF 
A 42° SWEPTBACK WING AT REYNOLDS NUMBERS 
UP TO 6.8 x 10 6 . G. Chester Furlong and Thomas 
V. Bollech. 1955. ii, 60p. diagrs., photos., tab. 
(NACA Rept. 1218. Combination of RM L8G22; 
TN 2487) 

DOWNWASH SURVEY BEHIND TWO LOW-ASPECT- 
RATIO VARIABLE-INCIDENCE WINGS IN COMBI- 
NATION WITH THREE DIFFERENT SIZE FUSE- 
LAGES AT A MACH NUMBER OF 0,25. Edward J. 
Hopkins and Norman E. So re n sen. March 1955. 54p. 
diagrs., photos., tab. (NACA RM A55A07) 



FLOW STUDIES ON FLAT -PLATE DELTA WINGS 
AT SUPERSONIC SPEED. William H. Michael, Jr. 
July 1955. 4 Op. diagrs., photos. (NACA TN 3472) 



VORTEX INTERFERENCE ON SLENDER AIR- 
PLANES. A Win H. Sacks. November 1955. 19p. 
diagr. (NACA TN 3525) 



FLOW STUDIES ON DROOPED-LEADING-EDGE 
DELTA WINGS AT SUPERSONIC SPEED. William 
H. Michael, Jr. January 1956. 29p. diagrs., 
photos. (NACA TN 3614) 



A THEORETICAL STUDY OF THE AERODYNAMICS 
OF SLENDER CRUCIFORM-WING ARRANGEMENTS 
AND THEIR WAKES. John R. Spreiter and Alvin H. 
Sacks. March 1956. i, 67p. diagrs., photos., tabs. 
(NACA TN 3528) 



LINEARIZED LIFTING-SURFACE AND LIFTING- 
LINE EVALUATIONS OF SIDEWASH BEHIND 
ROLLING TRIANGULAR WINGS AT SUPERSONIC 
SPEEDS. Percy J. Bobbitt. March 1956, 63p. 
diagrs. (NACA TN 3609) 



AN ANALYSIS OF ESTIMATED AND EXPERI- 
MENTAL TRANSONIC DOWNWASH CHARACTER- 
ISTICS AS AFFECTED BY PLAN FORM AND THICK- 
NESS FOR WING AND WING- FUSELAGE CONFIG- 
URATIONS. Joseph Weil, George S. Campbell and 
Margaret S. Diederlch. April 1956. 92p. diagrs., 
photos., tabs. (NACA TN 3628. Supersedes 
RM L52I22) 



DETERMINATION OF VORTEX PATHS BY SERIES 
EXPANSION TECHNIQUE WITH APPLICATION TO 
CRUCIFORM WINGS. Alberta Y. Alksne. 
April 1956. 40p. diagrs., photos. (NACA TN 3670) 



ANALYSIS AND COMPARISON WITH THEORY OF 
FLOW-FIELD MEASUREMENTS NEAR A LIFTING 
ROTOR IN THE LANGLEY FULL-SCALE TUNNEL. 
Harry H. Heyson. April 1956. 162p. diagrs., 
photos., tab. (NACA TN 3691) 



COMPARISON BETWEEN EXPERIMENTAL AND 
PREDICTED DOWNWASH AT A MACH NUMBER OF 
0.25 BEHIND A WING-BODY COMBINATION HAVING 
A TRIANGULAR WING OF ASPECT RATIO 2.0. 
Norman E. Sorensen and Edward J, Hopkins, May 
1956. 29p. diagrs., photos. (NACA TN 3720) 



(1.2.2.8) 
BOUNDARY LAYER 



SUBSONIC INVESTIGATION OF EFFECTS OF BODY 
INDENTATION ON ZERO-LIFT DRAG CHARACTER- 
ISTICS OF A 45° SWEPTBACK WING-BODY COMBI- 
NATION WITH NATURAL AND FIXED BOUNDARY- 
LAYER TRANSITION THROUGH A RANGE OF 
REYNOLDS NUMBER FROM 1 x 10 6 TO 8 x 10 6 . 
Gene J. Bingham and Albert L. Braslow. April 1954. 
lOp. diagrs., photos. (NACA RM L54B18a) 



INVESTIGATIONS AT SUPERSONIC SPEEDS OF 22 
TRIANGULAR WINGS REPRESENTING TWO AIR- 
FOIL SECTIONS FOR EACH OF 11 APEX ANGLES. 
Eugene S. Love. 1955. it, 60p. diagrs., photos., 
tabs. (NACA Rept. 1238. Supersedes RM L9D07) 



(1.2. 2.8. 1) 
Characteristics 



WIND-TUNNEL INVESTIGATION AT LOW SPEED OF 
A TWISTED AND CAMBERED WING SWEPT BACK 
63° WITH VORTEX GENERATORS AND FENCES. 
"James A. Weiberg and George B. McCullough. 
March 1952. 45p. diagrs., photos., 3 tabs, 
(NACARM A52A17) 



(1.2.2.8.2) 
Control 

WIRE CLOTH AS POROUS MATERIAL FOR 
TRANSPIRATION -COOL ED WALLS. E. R. G. 
Eckert, Martin R. Kinsler, and Reeves P. Cochran. . 
November 1951. 38p. diagrs., photos., tab. (NACA 
RM E51H23) 



EFFECT OF VERTICAL LOCATION OF A HORIZON- 
TAL TAIL ON THE STATIC LONGITUDINAL STA- 
BILITY CHARACTERISTICS OF A 45° SWEPTBACK- 
WING - FUSELAGE COMBINATION OF ASPECT 
RATIO 8 AT A REYNOLDS NUMBER OF 4.0 x 10 6 . 
Reino J. Salmi and William A. Jacques. January 
1952. 42p. diagrs., photos. (NACA RM L51J08) 



WIND-TUNNEL INVESTIGATION AT LOW SPEED OF 
A TWISTED AND CAMBERED WING SWEPT BACK 
63° WITH VORTEX GENERATORS AND FENCES. 
James A. Weiberg and George B. McCullough 
March 1952, 45p. diagrs., photos., 3 tabs. 
(NACA RM A52A17) 



50 



(1) AERODYNAMICS 



THE USE OF LEADING-EDGE AREA SUCTION TO 
INCREASE THE MAXIMUM LIFT COEFFICIENT OF 
A 35° SWEPT-BACK WING. Curt A. Holzhauser and 
Robert K. Martin. September 1952. 37p. diagrs., 
photo., 3 tabs. (NACA RM A52G17) 

WIND-TUNNEL INVESTIGATION OF STALL CON- 
TROL BY SUCTION THROUGH A POROUS LEADING 
EDGE ON A 37° SWEPTBACK WING OF ASPECT 
RATIO 6 AT REYNOLDS NUMBERS FROM 2.50xl0 6 
to 8.10 x 10 6 . Robert R. Graham and William A. 
Jacques. March 1953. 67p. diagrs., photo., 2 tabs. 
<NACA RM L52L05) 

FLIGHT INVESTIGATION OF THE EFFECTS OF A 
PARTIAL-SPAN LEADING-EDGE CHORD EXTEN- 
SION OF THE AERODYNAMIC CHARACTERISTICS 
OF A 35° SWEPT-WING FIGHTER AIRPLANE. 
Frederick H. Matteson and Rudolph D. Van Dyke; Jr. 
April 1954. 34p. diagrs., photos., tabs. 
(NACA RM A54B26) 

FLIGHT TESTS OF LEADING-EDGE AREA SUCTION 
ON A FIGHTER-TYPE AIRPLANE WITH A 35° 
SWEPTBACK WING. Richard S. Bray and Robert C. 
Innis. June 1955. 30p. diagrs., photos., tab. 
(NACA RM A55C07) 



ON THE PERMEABILITY OF POROUS MATERIALS. 
E. Carson Yates, Jr. January 1956. 31p. diagrs. 
(NACA TN 3596) 



EXPERIMENTAL INVESTIGATION OF AIR-FLOW 
UNIFORMITY AND PRESSURE LEVEL ON WIRE 
CLOTH FOR TRANSPIRATION-COOLING APPLI- 
CATIONS. Patrick L. Donoughe and Roy A. 
McKinnon. January 1956. 28p. diagrs., photos., 
tab. (NACA TN 3652. Supersedes RM E52E16) 



PERFORATED SHEETS AS A POROUS MATERUL 
FOR DISTRIBUTED SUCTION AND INJECTION. 
Robert E. Dannenberg, Bruno J. Gambucci, and 
James A. Weiberg. April 1956. 27p. diagrs., 
photos. (NACA TN 3669) 



A WIND-TUNNEL INVESTIGATION OF A 0.4-SCALE 
MODEL OF AN ASSAULT-TRANSPORT AIRPLANE 
WITH BOUNDARY-LAYER CONTROL APPLIED. 
Marvin P. Fink, Bennie W. Cocke, and Stanley 
Lipson. May 1956. 63p. diagrs., photos. 
(NACA RM L55G26a) 



51 



( 1 ) AERODYNAMICS 



(1.3) 
Bodies 



AERODYNAMIC INVESTIGATION OF A PARABOLIC 
BODY OF REVOLUTION AT MACH NUMBER OF 
1.92 AND SOME EFFECTS OF AN ANNULAR JET 
EXHAUSTING FROM THE BASE. Eugene S. Love. 
February 8, 1950. 75p. diagrs., photos., tab. 
(NACA RM L9K09) 



LIFT AND PITCHING- MOMENT INTERFERENCE 
BETWEEN A POINTED CYLINDRICAL BODY AND 
TRIANGULAR WINGS OF VARIOUS ASPECT RATIOS 
AT MACH NUMBERS OF 1.50 AND 2.02. Jack N. 
Nielsen, Elliott D. Katzen, and Kenneth K. Tang. 
September 12, 1950. 53p. diagrs., photos., tabs. 
(NACA RM A50F06) 



CHARACTERISTICS OF FLOW OVER INCLINED 
BODIES OF REVOLUTION. H. Julian Allen and 
Edward W. Perkins. March 5, 1951. 47p. diagrs., 
photos. (NACA RM A50L07) 



PRELIMINARY INVESTIGATION OF EFFECTIVE- 
NESS OF BASE BLEED IN REDUCING DRAG OF 
BLUNT -BASE BODIES IN SUPERSONIC STREAM. 
Edgar M. Cortright, Jr., and Albert H. Schroeder. 
March 9, 1951. 23p. diagrs., photos. 
(NACA RME51A26) 



DRAG INTERFERENCE BETWEEN A POINTED 
CYLINDRICAL BODY AND TRIANGULAR WINGS OF 
VARIOUS ASPECT RATIOS AT MACH NUMBERS OF 
1.50 AND 2.02. Elliott D. Katzen and George E. 
Kaattari. May 23, 1951. 45p. diagrs., photos., tabs. 
(NACA RM A51C27) 



AERODYNAMIC CHARACTERISTICS OF THE NACA 
RM-10 RESEARCH MISSILE IN THE AMES 1- BY 
3-FOOT SUPERSONIC WIND TUNNEL NO. 2 - 
PRESSURE AND FORCE MEASUREMENTS AT 
MACH NUMBERS OF 1.52 AND 1.98. Edward W. 
Perkins, Forrest E. Gowen and Leland H. Jorgensen. 
September 1951. 37p. diagrs. (NACA RM A51G13) 



TRANSONIC -WING INVESTIGATION IN THE 
LANGLEY 8-FOOT HIGH-SPEED TUNNEL AT HIGH 
SUBSONIC MACH NUMBERS AND AT A MACH NUM- 
BER OF 1.2. ANALYSIS OF PRESSURE DISTRIBU- 
TION OF WING-FUSELAGE CONFIGURATION HAV- 
ING A WING OF 45° SWEEPBACK, ASPECT RATIO 
4, TAPER RATIO 0.6, AND NACA 65A006 AIRFOIL 
SECTION. Donald L. Loving and Bruce B. 
Estabrooks. September 1951. 132p. diagrs., photos. 
(NACA RM L51F07) 



INVESTIGATION OF THE EFFECT OF A NACELLE 
AT VARIOUS CHORDWISE AND VERTICAL POSI- 
TIONS ON THE AERODYNAMIC CHARACTERISTICS 
AT HIGH SUBSONIC SPEEDS OF A 45° SWEPTBACK 
WING WITH AND WITHOUT A FUSELAGE. 
H. Norman Silvers, Thomas J. King, Jr., and 
Thomas B. Pasteur, Jr. September 1951. 71p. 
diagrs., photos., 3 tabs. (NACA RM L51H16) 



AN ANALYSIS OF THE PRESSURE DISTRIBUTION 
MEASURED ON A BODY OF REVOLUTION AT 
TRANSONIC SPEEDS IN THE SLOTTED TEST SEC- 
TION OF THE LANGLEY 8 -FOOT TRANSONIC 
TUNNEL. Bruce B. Estabrooks. June 1952. 42p. 
diagrs. (NACA RM L52D21a) 



INVESTIGATIONS AT SUPERSONIC SPEEDS OF THE 
BASE PRESSURE ON BODIES OF REVOLUTION 
WITH AND WITHOUT SWEPTBACK STABILIZING 
FINS. Eugene S. Love and Robert M. O'Donnell. 
December 1952. 66p. diagrs. , photos. (NACA 
RM L52J21a) 



WIND-TUNNEL INVESTIGATION AT LOW SPEED 
OF THE EFFECT OF VARYING THE RATIO OF 
BODY DIAMETER TO WING SPAN FROM 0.1 TO 0.8 
ON THE AERODYNAMIC CHARACTERISTICS IN 
PITCH OF A 45° SWEPTBACK -WING— BODY 
COMBINATION. Harold S. Johnson. November 
1953. 32p. diagrs.. photo., tab. 
(NACA RM L53J09a) 



AERODYNAMIC CHARACTERISTICS OF A CIRCU- 
LAR CYLINDER AT MACH NUMBER 6.66 AND 
ANGLES OF ATTACK UP TO 90°. Jim A. Penland. 
March 1954. 30p. diagrs., photos. 
(NACA RM L54A14) 



LONGITUDINAL STABILITY AND DRAG CHAR- 
ACTERISTICS OF A FIN-STABILIZED BODY OF 
REVOLUTION WITH A FINENESS RATIO OF 12 AS 
MEASURED BY THE FREE-FALL METHOD. 
MaxC. Kurbjun. June 1954. 19p. diagrs., photos., 
tab. (NACA RM L54E13) 



DRAG MEASUREMENTS ON A l/6-SCALE, FIN- 
LESS, STING-MOUNTED NACA RM-10 MISSILE IN 
FLIGHT AT MACH NUMBERS FROM 1.1 TO 4.04 
SHOWING SOME REYNOLDS NUMBER AND HEAT- 
ING EFFECTS. Robert O. Piland. October 1954. 
20p. diagrs., photos. (NACA RM L54H09) 



A UNIFIED TWO-DIMENSIONAL APPROACH TO 
THE CALCULATION OF THREE-DIMENSIONAL 
HYPERSONIC FLOWS, WITH APPLICATION TO 
BODIES OF REVOLUTION. A. J. Eggers, Jr. and 
Raymond C. Savin. 1955. ii, 27p. diagrs., tab. 
(NACA Rept. 1249. Supersedes TN 2811) 



COMPARISON OF THE EXPERIMENTAL AND 
THEORETICAL DISTRIBUTIONS OF LIFT ON A 
SLENDER INCLINED BODY OF REVOLUTION AT 
M = 2*. Edward W. Perkins and Donald M. Kuehn. 
May 1956, 39p. diagrs., photos., tabs. 
(NACA TN 3715. Supersedes RM A53E01) 



COMPARISON OF EXPERIMENTAL AND THEO- 
RETICAL NORMAL-FORCE DISTRIBUTIONS (IN- 
CLUDING REYNOLDS NUMBER EFFECTS) ON AN 
OGIVE-CYLINDER BODY AT MACH NUMBER 1.98. 
Edward W. Perkins and Leland H. Jorgensen. May 
1956. 50p. diagrs., tab. (NACA TN 3716. Super- 
sedes RM A54H23) 



52 



(1) AERODYNAMICS 

(1.3.1) 
THEORY 



AERODYNAMIC CHARACTERISTICS OF NACA RM- 
10 MISSILE IN 8- BY 6-FOOT SUPERSONIC WIND 
TUNNEL AT MACH NUMBERS FROM 1.49 TO 1.98. 
n - PRESENTATION AND ANALYSIS OF FORCE 
MEASUREMENTS. Fred T. Esenwein, Leonard J. 
Obery, and Carl F. Schueller. July 21, 1950. 34p 
diagrs., photo. (NACA RM E50D28) 

PRESSURE MEASUREMENTS ON A SHARPLY CON- 
VERGING FUSELAGE AFTERBODY WITH JET ON 
AND OFF AT MACH NUMBERS FROM 0.8 TO 1.6. 
William E. Stoney, Jr., and Ellis Katz. August 10, 
1950. 18p. diagrs., photos. (NACA RM L50F06) 



AERODYNAMIC CHARACTERISTICS OF NACA 
RM-10 MISSILE IN 8- BY 6-FOOT SUPERSONIC 
WIND TUNNEL AT MACH NUMBERS FROM 1.49 TO 
1.98. m - ANALYSIS OF FORCE DISTRIBUTION 
AT ANGLE OF ATTACK (STABILIZING FINS RE- 
MOVED). Roger W. Luidens and Paul C. Simon. 
December 12, 1950. 26p. diagrs. 
(NACA RM E50I19) 

FLOW SEPARATION AHEAD OF A BLUNT AXIALLY 
SYMMETRIC BODY AT MACH NUMBERS 1.76 TO 
2.10. W. E. Moeckel. December 1951. 12p. 
diagrs., photos. (NACA RM E51I25) 



PRESSURE DISTRIBUTIONS AT MACH NUMBERS 
FROM 0.6 TO 1.9 MEASURED IN FREE FLIGHT ON 
A PARABOLIC BODY OF REVOLUTION WITH 
SHARPLY CONVERGENT AFTERBODY. William E. 
Stoney, Jr. April 1952. 34p. diagrs., photos. 
(NACA RM L51L03) 



EFFECTS OF STABILIZING FINS AND A REAR- 
SUPPORT STING ON THE BASE PRESSURES OF A 
BODY OF REVOLUTION IN FREE FLIGHT AT 
MACH NUMBERS FROM 0.7 TO 1.3. Roger G. 
Hart. September 1952. 19p. diagrs., photos., tab. 
(NACA RM L52E06) 



COMPARISON OF MEASURED AND PREDICTED 
INDICATED ANGLES OF ATTACK NEAR THE 
FUSELAGES OF A TRIANGULAR-WING WIND- 
TUNNEL MODEL AND A SWEPT -WING FIGHTER 
AIRPLANE IN FLIGHT. Norman M. McFadden, 
JohnL. McCloud, HI, and Harry A. James. 
March 1953. 13p. diagrs. (NACA RM A53A15) 



THE BASE PRESSURE AT SUPERSONIC SPEEDS 
ON TWO-DIMENSIONAL AIRFOB^S AND BODIES OF 
REVOLUTION (WITH AND WITHOUT FINS) HAVING 
TURBULENT BOUNDARY LAYERS. Eugene S. Love. 
April 1953. 65p. diagrs., photos. > (NACA 
RM L53C02) 



WIND-TUNNEL INVESTIGATION AT LOW SPEED 
OF THE EFFECT OF VARYING THE RATIO OF 
BODY DIAMETER TO WING SPAN FROM 0.1 TO 0.8 
ON THE AERODYNAMIC CHARACTERISTICS IN 
PITCH OF A 45° SWEPTBACK- WING— BODY 
COMBINATION. Harold S. Johnson. November 
1953. 32p. diagrs.. photo., tab. 
(NACA RM L53J09a) 



A STUDY OF HYPERSONIC SMALL -DISTURBANCE 
THEORY. Milton D. Van Dyke. 1954. ii, 21p. 
diagrs. (NACA Rept. 1194. Formerly TN 3173) 



LONGITUDINAL STABILITY AND DRAG CHAR- 
ACTERISTICS OF A FIN-STABILIZED BODY OF 
REVOLUTION WITH A FINENESS RATIO OF 12 AS 
MEASURED BY THE FREE-FALL METHOD. 
Max C. Kurbjun. June 1954. 19p. diagrs., photos., 
tab. (NACA RM L54E13) 



DRAG MEASUREMENTS ON A l/6-SCALE, FIN- 
LESS, STING-MOUNTED NACA RM-10 MISSILE IN 
FLIGHT AT MACH NUMBERS FROM 1.1 TO 4.04 
SHOWING SOME REYNOLDS NUMBER AND HEAT- 
ING EFFECTS. Robert O. PUand. October 1954. 
20p. diagrs., photos. (NACA RM L54H09) 



AN INVESTIGATION OF THE CHARACTERISTICS OF 
THE NACA RM-10 (WITH AND WITHOUT FINS) IN 
THE LANGLEY 11-INCH HYPERSONIC TUNNEL AT 
A MACH NUMBER OF 6.9. William D. McCauley 
and William V. Feller. November 1954. 37p. 
diagrs., photos. (NACA RM L54I03) 



MINIMUM-DRAG DUCTED AND POINTED BODIES 
OF REVOLUTION BASED ON LINEARIZED SUPER- 
SONIC THEORY. Hermon M. Parker. 1955. ii, 
9p. diagrs. (NACA Rept. 1213. Supersedes 
TN 3189) 



ARRANGEMENT OF FUSIFORM BODIES TO RE- 
DUCE THE WAVE DRAG AT SUPERSONIC SPEEDS. 
Morris D. Friedman and Doris Cohen. 1955. ii, 
8p. diagrs. (NACA Rept. 1236. Supersedes 
RM A51I20; TN 3345) 



ON BOATTAIL BODIES OF REVOLUTION HAVING 
MINIMUM WAVE DRAG. Keith C. Harder and 
Conrad Rennemann, Jr. August 1955. 28p. diagrs. 
tab. (NACA TN 3478) 



AN APPROXIMATE SOLUTION FOR AXIALLY 
SYMMETRIC FLOW OVER A CONE WITH AN AT- 
TACHED SHOCK WAVE. Richard A. Hord. 
October 1955. 32p. diagrs. (NACA TN 3485) 



A SECOND-ORDER SHOCK-EXPANSION METHOD 
APPLICABLE TO BODIES OF REVOLUTION NEAR 
ZERO LIFT. Clarence A. Syvertson and David H. 
Dennis. January 1956. 57p. diagrs., tabs. 
(NACA TN 3527) 



ERROR IN AIRSPEED MEASUREMENT DUE TO 
THE STATIC -PRESSURE FIELD AHEAD OF AN 
AIRPLANE AT TRANSONIC SPEEDS. Thomas C. 
O'Bryan, Edward C. B. Danforth, and J, Ford 
Johnston. February 1956. 13p. diagrs., photos. 
(NACA Rept. 1239. Supersedes RM L9C25; 
RML50L28; RM L52A17) 



53 



(1) AERODYNAMICS 



LAMINAR FLOW ABOUT A ROTATING BODY OF 
REVOLUTION IN AN AXIAL AIRSTREAM. (Die 
laminare Stromung um einen axial angestrbmten 
rotierreden Drehkorper). H. Schlichting. 
(Abstract of paper presented at the Eighth Inter- 
national Mechanics Congress, Istanbul, August 
27, 1952). February 1956. 43p. diagrs., photo. 
(NACA TM 1415. Trans, from Ingenieur-Archiv. 
v. 21, no. 4, 1953, p. 227-244) 



BODIES OF REVOLUTION HAVING MINIMUM DRAG 
AT HIGH SUPERSONIC AIRSPEEDS. A. J. Eggers, 
Jr., Meyer M. Resnikoff, and David H. Dennis. 
February 1956. 38p. diagrs., photos. 
(NACA TN 3666. Supersedes RM A51K27; A52D24) 



FLOW OF GAS THROUGH TURBINE LATTICES. 
M. E. Deich. May 1956. 136p. diagrs., photos. 
(NACA TM 1393. Trans, of Russian book: 
Technical Gasdynamics, ch. 7, 1953, p. 312-420) 



COMPARISON OF EXPERIMENTAL AND THEO- 
RETICAL NORMAL-FORCE DISTRIBUTIONS (IN- 
CLUDING REYNOLDS NUMBER EFFECTS) ON AN 
OGIVE -CYLINDER BODY AT MACH NUMBER 1.98. 
Edward W. Perkins and Leland H. Jorgensen. May 
1956. 50p. diagrs., tab. (NACA TN 3716. Super- 
sedes RM A54H23) 



THEORETICAL WAVE DRAG OF SHROUDED AIR- 
FOILS AND BODIES. Paul F. Byrd. June 1956. 



40p. diagrs. (NACA TN 3718) 



(1.3.2) 
SHAPE VARIABLES 



FLIGHT INVESTIGATIONS AT HIGH -SUBSONIC, 
TRANSONIC, AND SUPERSONIC SPEEDS TO DE- 
TERMINE ZERO-LIFT DRAG OF FIN-STABILIZED 
BODIES OF REVOLUTION HAVING FINENESS 
RATIOS OF 12.5, 8.91, AND 6.04 AND VARYING 
POSITIONS OF MAXIMUM DIAMETER. Roger G. 
Hart and Ellis R. Katz. November 30, 1949. 36p. 
diagrs., photos. (NACA RM L9I30) 



AERODYNAMIC CHARACTERISTICS OF FOUR 
BODIES OF REVOLUTION SHOWING SOME EF- 
FECTS OF AFTERBODY SHAPE AND FINENESS 
RATIO AT FREE-STREAM MACH NUMBERS FROM 
1.50 TO 1.99. Robert J. Cohen. May 22, 1951. 31p. 
diagrs., tabs. (NACA RM E51C06) 



INVESTIGATIONS AT SUPERSONIC SPEEDS OF THE 
BASE PRESSURE ON BODIES OF REVOLUTION 
WITH AND WITHOUT SWEPTBACK STABILIZING 
FINS. Eugene S. Love and Robert M. O'Donnell. 
December 1952. 66p. diagrs. , photos. (NACA 
RM L52J21a) 



PRESSURE DISTRIBUTION AND PRESSURE DRAG 
FOR A HEMISPHERICAL NOSE AT MACH NUM- 
BERS 2.05. 2.54, AND 3.04. Leo T. Chauvin. 
December 1952. 14p. diagrs., photos. 
(NACA RM L52K06) 



THE BASE PRESSURE AT SUPERSONIC SPEEDS 
ON TWO-DIMENSIONAL AIRFOILS AND BODIES OF 
REVOLUTION (WITH AND WITHOUT HNS) HAVING 
TURBULENT BOUNDARY LAYERS. Eugene S. Love. 
April 1953. 65p. diagrs., photos. (NACA 
RM L53C02) 



AN EXPERIMENTAL AND THEORETICAL INVES- 
TIGATION AT HIGH SUBSONIC SPEEDS OF THE 
EFFECTS OF HORIZONTAL-TAIL HEIGHT ON THE 
AERODYNAMIC CHARACTERISTICS IN SIDESLIP 
OF AN UNSWEPT, UNTAPERED TAIL ASSEMBLY. 
Harleth G. Wiley and Donald R. Riley. December 
1953. 71p. diagrs., tab. (NACA RM L53J19) 



SUBSONIC INVESTIGATION OF EFFECTS OF BODY 
INDENTATION ON ZERO-LIFT DRAG CHARACTER- 
ISTICS OF A 45° SWEPTBACK WING- BODY COMBI- 
NATION WITH NATURAL AND FIXED BOUNDARY- 
LAYER TRANSITION THROUGH A RANGE OF 
REYNOLDS NUMBER FROM 1 x 10 6 TO 8 x 10 6 . 
Gene J. Bingham and Albert L. Braslow. April 1954. 
lOp. diagrs., photos. (NACA RM L54B18a) 



MINIMUM-DRAG DUCTED AND POINTED BODIES 
OF REVOLUTION BASED ON LINEARIZED SUPER- 
SONIC THEORY. Hermon M. Parker. 1955. li, 
9p. diagrs. (NACA Rept. 1213. Supersedes 
TN 3189) 



APPLICATION OF WING-BODY THEORY TO DRAG 
REDUCTION AT LOW SUPERSONIC SPEEDS. 
Barrett S. Baldwin, Jr. , and Robert R. Dickey. 
January 1955. 42p. (NACA RM A54J19) 

ON BOATTAIL BODIES OF REVOLUTION HAVING 
MINIMUM WAVE DRAG. Keith C. Harder and 
Conrad Rennemann, Jr. August 1955. 28p. diagrs., 
tab. (NACA TN 3478) 



FLIGHT INVESTIGATION AT MACH NUMBERS 
FROM 0.8 TO 1.5 TO DETERMINE THE EFFECTS 
OF NOSE BLUNTNESS ON THE TOTAL DRAG OF 
TWO FIN-STABILIZED BODIES OF REVOLUTION. 
Roger G. Hart. December 1955. lip. diagrs., 
photos., tabs. (NACA TN 3549. Supersedes 
RM L50I08a) 



WING-BODY COMBINATIONS WITH CERTAIN GEO- 
METRIC RESTRAINTS HAVING LOW ZERO-LIFT 
WAVE DRAG AT LOW SUPERSONIC MACH NUM- 
BERS. Harvard Lomax. February 1956. 32p. 
diagrs. (NACA TN 3667) 



'INVESTIGATION AT HIGH SUBSONIC SPEEDS OF A 
BODY-CONTOURING METHOD FOR ALLEVIATING 
THE ADVERSE INTERFERENCE AT THE ROOT OF 
A SWEPTBACK WING. John B. McDevitt and 
William M. Haire. April 1956. 38p. diagrs., 
photos. (NACA TN 3672. Supersedes RM A54A22) 



INVESTIGATION AT SUPERSONIC SPEEDS OF THE 
VARIATION WITH REYNOLDS NUMBER AND MACH 
NUMBER OF THE TOTAL, BASE, AND SKIN- 
FRICTION DRAG OF SEVEN BOATTAIL BODIES OF 
REVOLUTION DESIGNED FOR MINIMUM WAVE 
DRAG. August F. Bromm, Jr. and Julia M. 
Goodwin. June 1956. 20p. diagrs., photo. 
(NACA TN 3708. Supersedes RM L53X29b) 



54 



(1) AERODYNAMICS 



(1.3.2.1) 
FINENESS RATIO 



INVESTIGATION OF THE EFFECTS OF GEO- 
METRIC CHANGES IN AN UNDERWING PYLON- 
SUSPENDED EXTERNAL-STORE INSTALLATION 
ON THE AERODYNAMIC CHARACTERISTICS OF A 
45° SWEPTBACK WING AT HIGH SUBSONIC 
SPEEDS. Kenneth P. Spreemann and William J. 
Alford, Jr. March 5, 1951. 91p. diagrs., photos., 
tabs. (NACA RM L50L12) 



AERODYNAMIC CHARACTERISTICS OF FOUR 
BODIES OF REVOLUTION SHOWING SOME EF- 
FECTS OF AFTERBODY SHAPE AND FINENESS 
RATIO AT FREE-STREAM MACH NUMBERS FROM 
1.50 TO 1.99. Robert J. Cohen. May 22, 1951. 31p. 
diagrs., tabs. (NACA RM E51C06) 



PRESSURE MEASUREMENTS ON A BODY OF REVO- 
LUTION IN THE LANGLEY 16-FOOT TRANSONIC 
TUNNEL AND A COMPARISON WITH FREE-FALL 
DATA. Joseph M. Hallissy, Jr. March 1952. 19p. 
diagrs. (NACA RM L51L07a) 



INVESTIGATIONS AT SUPERSONIC SPEEDS OF THE 
BASE PRESSURE ON BODIES OF REVOLUTION 
WITH AND WITHOUT SWEPTBACK STABILIZING 
FINS, Eugene S. Love and Robert M. O'Donnell. 
December 1952. 66p. diagrs. , photos. (NACA 
RM L52J21a) 



INVESTIGATION OF REYNOLDS NUMBER EF- 
FECTS FOR A SERIES OF CONE-CYLINDER 
BODIES AT MACH NUMBERS OF 1.62, 1.93, AND 
2.41. Carl E. Grigsby and Edmund L. Ogburn. 
October 1953. 20p. diagrs., photos. (NACA 
RM L53H21) 



WIND-TUNNEL INVESTIGATION AT LOW SPEED 
OF THE EFFECT OF VARYING THE RATIO OF 
BODY DIAMETER TO WING SPAN FROM 0.1 TO 08 
ON THE AERODYNAMIC CHARACTERISTICS IN 
PITCH OF A 45° SWEPTBACK-WING-BODY 
COMBINATION. Harold S. Johnson. November 
1953. 32p. diagrs.. photo., tab. 
(NACA RM L53J09a) 



EFFECTS OF WING POSITION AND FUSELAGE 
SIZE ON THE LOW-SPEED STATIC AND ROLLING 
STABILITY CHARACTERISTICS OF A DELTA-WING 
MODEL. Alex Goodman and David F. Thomas, Jr. 
1955, ii, 31p. diagrs., photos., tabs. 
(NACA Rept. 1224. Supersedes TN 3063) 



A SECOND-ORDER SHOCK-EXPANSION METHOD 
APPLICABLE TO BODIES OF REVOLUTION NEAR 
ZERO LIFT. Clarence A. Syvertson and David H. 
Dennis. January 1956. 57p. diagrs., tabs. 
(NACA TN 3527) 



ERROR IN AIRSPEED MEASUREMENT DUE TO 
THE STATIC-PRESSURE FIELD AHEAD OF AN 
AIRPLANE AT TRANSONIC SPEEDS. Thomas C. 
O' Bryan, Edward C. B, Danforth, and J. Ford 
Johnston. February 1956. 13p. diagrs., photos. 
(NACA Rept. 1239. Supersedes RM L9C25; 
RML50L28; RM L52A17) 



(1.3.2.2) 
CROSS SECTION 

EFFECT OF A PILOT'S CANOPY ON THE DRAG 
OF AN NACA RM-2 DRAG RESEARCH MODEL IN 
FLIGHT AT TRANSONIC AND SUPERSONIC 
SPEEDS. Paul E. Purser. April 20, 1948. 7p. 
diagrs., photos. (NACA RM L7L22) 



FLIGHT INVESTIGATION AT MACH NUMBERS 
FROM 0.8 TO 1.5 OF THE DRAG OF A CANOPY 
LOCATED AT TWO POSITIONS ON A PARABOLIC 
BODY OF REVOLUTION. Clement J. Welsh and 
John D. Morrow. March 15, 1951. 15p. diagrs., 
photos., tabs. (NACA RM L51A29) 



THE EFFECT ON ZERO-LIFT DRAG OF AN IN- 
DENTED FUSELAGE OR A THICKENED WING-ROOT 
MODIFICATION TO A 45° SWEPTBACK WING-BODY 
CONFIGURATION AS DETERMINED BY FLIGHT 
TESTS AT TRANSONIC SPEEDS. William B. 
Pepper. September 1951. 20p. diagrs., photos., 
2 tabs. (NACA RM L51F15) 



SOME EFFECTS OF BODY CROSS-SECTIONAL 
SHAPE, INCLUDING A SUNKEN-CANOPY DESIGN, 
ON DRAG AS SHOWN BY ROCKET-POWERED- 
MODEL TESTS AT MACH NUMBERS FROM 0.8 TO 
1.5. William E. Stoney, Jr., and Leonard W. 
Putland. July 1952. 15p. diagrs., photos. 
(NACA RM L52D07) 



WIND-TUNNEL INVESTIGATION AT LOW SPEED 
OF EFFECT OF SIZE AND POSITION OF CLOSED 
AIR DUCTS ON STATIC LONGITUDINAL AND 
STATIC LATERAL STABILITY CHARACTERISTICS 
OF UNSWEPT-MIDWING MODELS HAVING WINGS 
OF ASPECT RATIO 2, 4, AND 6. Byron M. Jaquet 
and James L. Williams. September 1955. 45p. 
diagrs., photos., tabs. (NACA TN 3481) 



EXPERIMENTAL INVESTIGATION AT LOW SPEED 
OF EFFECTS OF FUSELAGE CROSS SECTION ON 
STATIC LONGITUDINAL AND LATERAL STABILITY 
CHARACTERISTICS OF MODELS HAVING 0° AND 
45° SWEPTBACK SURFACES. William Letko and 
James L. Williams. December 1955. 45p. diagrs., 
tabs. (NACA TN 3551) 



WIND-TUNNEL INVESTIGATION OF EFFECTS OF 
FUSELAGE CROSS -SECTIONAL SHAPE, FUSE- 
LAGE BEND, AND VERTICAL-TAIL SIZE ON DI- 
RECTIONAL CHARACTERISTICS OF 
NONOVERLAP-TYPE HELICOPTER FUSELAGE 
MODELS WITHOUT ROTORS. James L. Williams. 
March 1956. 39p. diagrs., photos. 
(NACA TN 3645) 



55 



(1) AERODYNAMICS 



(1.3.2.3) 
THICKNESS DISTRIBUTION 



FLIGHT INVESTIGATIONS AT HIGH-SUBSONIC, 
TRANSONIC, AND SUPERSONIC SPEEDS TO DE- 
TERMINE ZERO-LIFT DRAG OF FIN-STABILIZED 
BODIES OF REVOLUTION HAVING FINENESS 
RATIOS OF 12.5, 8.91, AND 6.04 AND VARYING 
POSITIONS OF MAXIMUM DIAMETER. Roger G. 
Hart and Ellis R. Katz. November 30, 1949. 36p. 
diagrs., photos. (NACA RM L9I30) 



FLIGHT INVESTIGATION AT MACH NUMBERS 
FROM 0.8 TO 1.5 TO DETERMINE THE EFFECTS 
OF NOSE BLUNTNESS ON THE TOTAL DRAG OF 
TWO FIN-STABILIZED BODIES OF REVOLUTION. 
Roger G. Hart. December 1955. lip. diagrs., 
photos., tabs. (NACA TN 3549. Supersedes 
RM L50I08a) 



(1.3.2.4) 
SURFACE CONDITIONS 



PRELIMINARY FREE-FLIGHT INVESTIGATION OF 
THE EFFECTS OF RIVETS AND LAP JOINTS ON 
THE DRAG OF BODIES AT ZERO LIFT AT SUPER- 
SONIC MACH NUMBERS TO 2.1 . Russell N. Hopko. 
August 1952. 12p. diagrs., photos., tab. 
(NACA RM L52F09) 



INVESTIGATION OF REYNOLDS NUMBER EF- 
FECTS FOR A SERIES OF CONE-CYLINDER 
BODIES AT MACH NUMBERS OF 1.62, 1.93, AND 
2.41. Carl E. Grigsby and Edmund L. Ogburn. 
October 1953. 20p. diagrs., photos. (NACA 
RM L53H21) 



AN INVESTIGATION OF THE EFFECTS OF HEAT 
TRANSFER ON BOUNDARY- LAYER TRANSITION ON 
A PARABOLIC BODY OF REVOLUTION (NACA RM- 
10) AT A MACH NUMBER OF 1.61. K. R. Czarneckl 
and Archibald R. Sinclair. 1955. lip. diagrs., 
photos., tab. (NACA Rept. 1240. Supersedes 
TN 3165 and TN 3166) 



A STUDY OF BOUNDARY-LAYER TRANSITION AND 
SURFACE TEMPERATURE DISTRIBUTIONS AT 
MACH 3.12. Paul F. Brinich. July 1955. 39p. 
diagrs., photo. (NACA TN 3509) 



ACOUSTIC RADIATION FROM TWO-DIMENSIONAL 
RECTANGULAR CUTOUTS IN AERODYNAMIC 
SURFACES. K. Krishnamurty, California Institute 
of Technology. August 1955. 33p. diagrs., photos. 
(NACA TN 3487) 



SOME MEASUREMENTS OF FLOW IN A RECTAN- 
GULAR CUTOUT. Anatol Roshko, California 
Institute of Technology. August 1955. 21p. diagrs. 
(NACA TN 3488) 



FLIGHT INVESTIGATION OF THE SURFACE- 
PRESSURE DISTRIBUTION AND THE FLOW FIELD 
AROUND A CONICAL AND TWO SPHERICAL NON- 
ROTATING FULL-SCALE PROPELLER SPINNERS. 
Jerome B. Hammack, Milton L. Windier, and 
Elwood F. Scheithauer. September 1955. 36p. 
diagrs., photos. (NACA TN 3535) 



EFFECT OF LEADING-EDGE GEOMETRY ON 
BOUNDARY-LAYER TRANSITION AT MACH 3.1. 
Paul F. Brinich. March 1956. 44p. diagrs., tabs. 
(NACA TN 3659) 



(1.3.2.5) 

PROTUBERANCES 

EFFECT OF A PILOT'S CANOPY ON THE DRAG 
OF AN NACA RM-2 DRAG RESEARCH MODEL IN 
FLIGHT AT TRANSONIC AND SUPERSONIC 
SPEEDS. Paul E. Purser. April 20, 1948, 7p. 
diagrs., photos. (NACA RM L7L22) 



EFFECT OF WINDSHIELD SHAPE OF A PILOT'S 
CANOPY ON THE DRAG OF AN NACA RM-2 DRAG 
RESEARCH MODEL IN FLIGHT AT TRANSONIC 
SPEEDS. Sidney R. Alexander. July 21, 1948. 
6p. diagrs. (NACA RM L8E04) 



FLIGHT INVESTIGATION AT MACH NUMBERS 
FROM 0.8 TO 1.5 OF THE DRAG OF A CANOPY 
LOCATED AT TWO POSITIONS ON A PARABOLIC 
BODY OF REVOLUTION. Clement J. Welsh and 
John D, Morrow. March 15, 195i. 15p. diagrs., 
photos., tabs. (NACA RM L51A29) 



FLOW SEPARATION AHEAD OF A BLUNT AXIALLY 
SYMMETRIC BODY AT MACH NUMBERS 1.76 TO 
2.10. W. E. Moeckel. December 1951. 12p. 
diagrs., photos. (NACA RM E51I25) 



PRELIMINARY FREE-FLIGHT INVESTIGATION OF 
THE EFFECTS OF RIVETS AND LAP JOINTS ON 
THE DRAG OF BODIES AT ZERO LIFT AT SUPER- 
SONIC MACH NUMBERS TO 2.1 . Russell N. Hopko. 
August 1952. 12p. diagrs., photos., tab. 
(NACA RM L52F09) 



A STUDY OF BOUNDARY-LAYER TRANSITION AND 
SURFACE TEMPERATURE DISTRIBUTIONS AT 
MACH 3.12. Paul F. Brinich. July 1955. 39p. 
diagrs., photo. (NACA TN 3509) 



WIND-TUNNEL INVESTIGATION AT LOW SPEED 
OF EFFECT OF SIZE AND POSITION OF CLOSED 
AIR DUCTS ON STATIC LONGITUDINAL AND 
STATIC LATERAL STABILITY CHARACTERISTICS 
OF UNSWEPT-MIDWING MODELS HAVING WINGS 
OF ASPECT RATIO 2, 4, AND 6. Byron M. Jaquet 
and James L. Williams. September 1955. 45p. 
diagrs., photos., tabs. (NACA TN 3481) 



56 



(1) AERODYNAMICS 



EFFECT OF PNEUMATIC DE-ICERS AND ICE 
FORMATIONS ON AERODYNAMIC CHARACTERIS- 
TICS OF AN AIRFOIL. Dean T. Bowden. February 
1956. 59p. diagrs., photos. (NACA TN 3564^ 



EFFECT OF LEADING-EDGE GEOMETRY ON 
BOUNDARY-LAYER TRANSITION AT MACH 3.1. 
Paul F. Brinich. March 1956. 44p. diagrs., tabs. 
(NACA TN 3659) 



THE FLOW PAST AN UNSWEPT- AND A SWEPT - 
WING— BODY COMBINATION AND THEIR EQUIVA- 
LENT BODIES OF REVOLUTION AT MACH NUM- 
BERS NEAR 1.0. Walter F. Linda ey. June 1956. 
18p. diagrs. , photos. (NACA TN 3703. Supersedes 
RM L54A28a) 



(1.3.3) 
CANOPIES 



EFFECT OF A PILOT'S CANOPY ON THE DRAG 
OF AN NACA RM-2 DRAG RESEARCH MODEL IN 
FLIGHT AT TRANSONIC AND SUPERSONIC 
SPEEDS. Paul E. Purser. April 20, 1948. 7p. 
diagrs., photos. (NACA RM L7L22) 



EFFECT OF WINDSHIELD SHAPE OF A PILOT'S 
CANOPY ON THE DRAG OF AN NACA RM-2 DRAG 
RESEARCH MODEL IN FLIGHT AT TRANSONIC 
SPEEDS. Sidney R. Alexander. July 21, 1948. 
6p. diagrs. (NACA RM L8E04) 



FLIGHT INVESTIGATION AT MACH NUMBERS 
FROM 0.8 TO 1.5 OF THE DRAG OF A CANOPY 
LOCATED AT TWO POSITIONS ON A PARABOLIC 
BODY OF REVOLUTION. Clement J. Welsh and 
John D. Morrow. March 15, 1951. 15p. diagrs., 
photos., tabs. (NACA RM L51A29) 



SOME EFFECTS OF BODY CROSS-SECTIONAL 
SHAPE, INCLUDING A SUNKEN-CANOPY DESIGN, 
ON DRAG AS SHOWN BY ROCKET-POWERED- 
MODEL TESTS AT MACH NUMBERS FROM 0.8 TO 
1.5. William E. Stoney, Jr., and Leonard W. 
Putland. July 1952. 15p. diagrs., photos. 
(NACA RM L52D07) 



(1.3.4) 
DUCTED BODIES 



PRELIMINARY INVESTIGATION OF EFFECTIVE- 
NESS OF BASE BLEED IN REDUCING DRAG OF 
BLUNT -BASE BODIES IN SUPERSONIC STREAM. 
Edgar M. Cortright, Jr., and Albert H. Schroeder. 
March 9, 1951. 23p. diagrs., photos. 
(NACA RM E51A26) 



CHARACTERISTICS OF FOUR NOSE INLETS AS 
MEASURED AT MACH NUMBERS BETWEEN 1.4 
AND 2.0. George B. Brajnikoff and Arthur W. 
Rogers. June 25, 1951. 48p. diagrs., photos. 
(NACARM A51C12* 



TRANSONIC FLIGHT TESTS TO DETERMINE 
ZERO-LIFT DRAG AND PRESSURE RECOVERY OF 
NACELLES LOCATED AT THE WING TIPS ON A 
45° SWEPTBACK WING AND BODY COMBINATION. 
Sherwood Hoffman and William B. Pepper, Jr. 
January 1952. 21p. diagrs., photos., tabs. 
(NACA RML51K02) 



FLIGHT DETERMINATION OF DRAG OF NORMAL - 
SHOCK NOSE INLETS WITH VARIOUS COWLING 
PROFILES AT MACH NUMBERS FROM 0.9 TO 1.5. 
R. I. Sears, C. F. Merlet, and L. W. Putland. 
October 1953. 36p. diagrs., photos., tabs. (NACA 
RM L53I25a) 



DYNAMIC STABILITY AND CONTROL CHARACTER- 
ISTICS OF A DUCTED-FAN MODEL IN HOVERING 
FLIGHT. Robert H. Kirby. April 1954. 16p. 
diagrs., photos. (NACA RM L54C18) 



SOME INTERNAL-FLOW CHARACTERISTICS AT 
ZERO FLIGHT SPEED OF AN ANNULAR SUPER- 
SONIC INLET AND AN OPEN-NOSE INLET WITH 
SHARP AND ROUNDED LIPS. Joseph R. MUillo. 
July 1954. 23p. diagrs., photo. 
(NACA RM L54E19) 



SOME INTERNAL-FLOW CHARACTERISTICS OF 
SEVERAL AXISYMMETRICAL NACA 1 -SERIES 
NOSE AIR INLETS AT ZERO FLIGHT SPEED. 
Carroll R. Bryan and Frank F. Fleming. July 1954. 
30p. diagrs., photos. (NACA RM L54E19a) 



ESTIMATION OF INLET LIP FORCES AT SUBSONIC 
AND SUPERSONIC SPEEDS. W. E. Moeckel. June 
1955. 12p. diagrs. (NACA TN 3457) 



FLIGHT DETERMINATION OF THE DRAG AND 
PRESSURE RECOVERY OF AN NACA 1-40-^50 NOSE 
INLET AT MACH NUMBERS FROM 0.9 TO 1.8. 
R. I. Sears and C. F. Merlet. July 1955. 30p. 
diagrs., photos., 2 tabs. (NACA TN 3218. Formerly 
RM L50L18) 



(1.3.4. 1) 
NOSE SHAPE 



WIND-TUNNEL INVESTIGATION OF A TAILLESS 
TRIANGULAR-WING FIGHTER AIRCRAFT AT 
MACH NUMBERS FROM 0.5 TO 1.5. Leslie F. 
Lawrence and James L. Summers. June 24, 1949. 
56p. diagrs., photos., tab. (NACA RM A9B16) 



57 



(1) AERODYNAMICS 



PRELIMINARY DATA ON THE EFFECT OF BODY- 
NOSE BLUNTNESS ON THE DRAG AND PRESSURE 
RECOVERY OF A SIDE-INLET-BODY COMBINA- 
TION AT MACH NUMBERS OF 1.4 AND 1.7. 
John F. Stroud and Warren E. Anderson. April 25, 
1951. 13p. diagrs., photos. (NACA RM A51A09) 



FLIGHT DETERMINATION OF DRAG OF NORMAL- 
SHOCK NOSE INLETS WITH VARIOUS COWLING 
PROFILES AT MACH NUMBERS FROM 0.9 TO 1.5. 
R. I. Sears, C. F. Merlet, and L. W. Putland. 
October 1953. 36p. diagrs., photos., tabs. (NACA 
RM L53I25a) 



THEORETICAL AND EXPERIMENTAL ANALYSIS 
OF LOW-DRAG SUPERSONIC INLETS HAVING A 
CIRCULAR CROSS SECTION AND A CENTRAL 
BODY AT MACH NUMBERS OF 3. 30, 2. 75, AND 
2. 45. Antonio Ferri and Louis M. Nucci. 1954. 
ii, 37p. diagrs., photos. (NACA Rept. 1189. 
Supersedes RM L8H13) 



SOME INTERNAL-FLOW CHARACTERISTICS AT 
ZERO FLIGHT SPEED OF AN ANNULAR SUPER- 
SONIC INLET AND AN OPEN-NOSE INLET WITH 
SHARP AND ROUNDED LIPS. Joseph R. MUillo. 
July 1954. 23p. diagrs., photo. 
(NACA RM L54E19) 



MINIMUM-DRAG DUCTED AND POINTED BODIES 
OF REVOLUTION BASED ON LINEARIZED SUPER- 
SONIC THEORY. Hermon M. Parker. 1955. ii, 
9p. diagrs. (NACA Rept. 1213. Supersedes 
TN 3189) 



FLIGHT DETERMINATION OF THE DRAG AND 
PRESSURE RECOVERY OF AN NACA 1-40-250 NOSE 
INLET AT MACH NUMBERS FROM 0.9 TO 1.8. 
R. I. Sears and C. F. Merlet. July 1955. 30p. 
diagrs., photos., 2 tabs. (NACA TN 3218. Formerly 
RM L50L18) 



(1.3.4.3) 
SIDE INLETS 

EXPERIMENTAL INVESTIGATION AT SUPERSONIC 
SPEEDS OF TWIN-SCOOP DUCT INLETS OF EQUAL 
AREA. I. - AN INLET ENCLOSING 61.5 PERCENT 
OF THE MAXIMUM CIRCUMFERENCE OF THE 
FOREBODY. Wallace F. Davis and David L. 
Goldstein. January 21, 1948. 16p. diagrs.. photos. 
(NACA RM A7J27) 



EXPERIMENTAL INVESTIGATION AT SUPERSONIC 
SPEEDS OF TWIN-SCOOP DUCT INLETS OF EQUAL 
AREA. II - EFFECTS OF SLOTS UPON AN INLET 
ENCLOSING 61.5 PERCENT OF THE MAXIMUM 
CIRCUMFERENCE OF THE FOREBODY. Wallace F. 
Davis and David L. Goldstein. June 9, 1948. 15p. 
diagrs., photos. (NACA RM A8C11) 



EXPERIMENTAL INVESTIGATION AT SUPERSONIC 
SPEEDS OF TWIN-SCOOP DUCT INLETS OF EQUAL 
AREA. HI - INLET ENCLOSING 37.2 PERCENT OF 
THE MAXIMUM CIRCUMFERENCE OF THE FORE- 
BODY. Wallace F. Davis and Sherman S. Edwards. 
July 22, 1948. 25p. diagrs., photos. 
(NACA RM A8E04) 



EXPERIMENTAL INVESTIGATION AT SUPERSONIC 
SPEEDS OF TWIN-SCOOP DUCT INLETS OF EQUAL 
AREA. IV - SOME EFFECTS OF INTERNAL DUCT 
SHAPE UPON AN INLET ENCLOSING 37.2 PERCENT 
OF THE FOREBODY CIRCUMFERENCE. Wallace F. 
Davis, Sherman S. Edwards, and George B. 
Brajnikoif. March 15, 1949. 21p. diagrs., photos. 
(NACA RM A9A31) 



SOME LOW-SPEED CHARACTERISTICS OF AN 
AIR-INDUCTION SYSTEM HAVING SCOOP-TYPE 
INLETS WITH PROVISIONS FOR BOUNDARY- 
LAYER CONTROL. Earl C. Watson. August 1951. 
42p. diagrs., photos., tab. (NACA RM A51F15) 



EXPERIMENTAL INVESTIGATION OF INTERNAL- 
FLOW CHARACTERISTICS OF FORWARD UNDER - 
SLUNG FUSELAGE SCOOPS WITH UNSWEPT AND 
SWEPTBACK ENTRANCE AT MACH NUMBERS OF 
1.41 TO 1.96. Robert W. Boswinkle, Jr., and 



mcauc ii. ivm 



««14.-U n 11 



tA.r\ nhnino 



diagrs. (NACA RM L52A24) 



PRESSURE AND FORCE CHARACTERISTICS AT 
TRANSONIC SPEEDS OF A SUBMERGED 
DIVERGENT- WALLED AIR INLET ON A BODY OF 
REVOLUTION. John A. Braden and P. Kenneth 
Pierpont. May 1953. 65p. photos., diagrs., tabs. 
(NACARML53C13) 



CHARTS OF BOUNDARY-LAYER MASS FLOW AND 
MOMENTUM FOR INLET PERFORMANCE ANALY- 
SIS MACH NUMBER RANGE, 0.2 TO 5.0. Paul C. 
Simon and Kenneth L. Kowalski. November 1955. 
32p. diagrs., tab. (NACA TN 3583) 



(1.3.4.4) 
SIDE EXITS 



AN INVESTIGATION OF THE DISCHARGE AND 
DRAG CHARACTERISTICS OF AUXILIARY -AIR 
OUTLETS DISCHARGING INTO A TRANSONIC 
STREAM. Paul E. Dewey and Allen R. Vick. July 
1955. 38p. diagrs., photos. (NACA TN 3466) 



SUMMARY OF SCALE-MODEL THRUST -REVERSER 
INVESTIGATION. John H. Povolny, Fred W. 
Steffen, and Jack G. McArdle. February 1956. 
49p. diagrs., photos. (NACA TN 3664) 



58 



(1) AERODYNAMICS 



(M) 
Internal Aerodynamics 



PRELIMINARY INVESTIGATION OF EFFECTIVE- 
NESS OF BASE BLEED IN REDUCING DRAG OF 
BLUNT -BASE BODIES IN SUPERSONIC STREAM. 
Edgar M. Cortright, Jr., and Albert H. Schroeder. 
March 9, 1951. 23p. diagrs., photos. 
(NACA RM E51A26) 



COMPARISON OF LOCKED-ROTOR AND WIND- 
MILLING DRAG CHARACTERISTICS OF AN AXIAL- 
FLOW -COMPRESSOR TYPE TURBOJET ENGINE. 
K. R. Vincent, S. C. Huntley, and H. D. Wilsted. 
January 1952. lOp. diagrs. (NACA RM E51K15) 



EFFECT OF TRANSVERSE BODY FORCE ON CHAN- 
NEL FLOW WITH SMALL HEAT ADDITION. Simon 
Ostrach and Franklin K. Moore. February 1956. 
31p. diagrs. (NACA TN 3594) 



(1.4.1) 
AIR INLETS 



TRANSONIC FLIGHT TESTS TO DETERMINE 
ZERO-LIFT DRAG AND PRESSURE RECOVERY OF 
NACELLES LOCATED AT THE WING TIPS ON A 
45° SWEPTBACK WING AND BODY COMBINATION. 
Sherwood Hoffman and William B. Pepper, Jr. 
January 1952. 21 p. diagrs., photos., tabs, 
(NACA RM L51K02) 



PERFORMANCE OF AIR INLETS AT TRANSONIC 
AND LOW SUPERSONIC SPEEDS. Mark R. Nichols 
and Robert E. Pendley. February 1952. 22p. 
diagrs. (NACA RM L52A07) 



AN ANALYTICAL STUDY OF THE COMPARATIVE 
PERFORMANCE OF FOUR AIR-INDUCTION SYS- 
TEMS FOR TURBOJET-POWERED AIRPLANES 
DESIGNED TO OPERATE AT MACH NUMBERS UP 
TO 1.5. James R. Blackaby. June 1952. 38p. 
diagrs. (NACA RM A52C14) 



FLIGHT DETERMINATION OF DRAG OF NORMAL - 
SHOCK NOSE INLETS WITH VARIOUS COWLING 
PROFILES AT MACH NUMBERS FROM 0.9 TO 1.5. 
R. I. Sears, C. F. Merlet, and L. W. Putland. 
October 1953. 36p. diagrs., photos., tabs. (NACA 
RM L53I25a) 



THEORETICAL AND EXPERIMENTAL INVESTIGA- 
TION OF ADDITIVE DRAG. Merwin SibuUdn. 1954. 
U, 12p. diagrs, (NACA Rept. 1187. Formerly 
RM E51B13) 



THEORETICAL PERFORMANCE CHARACTERIS- 
TICS OF SHARP-LD? INLETS AT SUBSONIC 
SPEEDS. Evan A. Fradenburgh and DeMarquis D. 
Wyatt. 1954. ii, 8p. diagrs. (NACA Rept. 1193. 
Formerly TN 3004) 



SOME INTERNAL-FLOW CHARACTERISTICS AT 
ZERO FLIGHT SPEED OF AN ANNULAR SUPER- 
SONIC INLET AND AN OPEN-NOSE INLET WITH 
SHARP AND ROUNDED LIPS. Joseph R. Milillo. 
July 1954. 23p. diagrs., photo. 
(NACA RM L54E19) 



FLIGHT DETERMINATION OF THE DRAG AND 
PRESSURE RECOVERY OF AN NACA 1-40-250 NOSE 
INLET AT MACH NUMBERS FROM 0.9 TO 1.8. 
R. I. Sears and C. F. Merlet. July 1955. 30p. 
diagrs., photos., 2 tabs. (NACA TN 3218. Formerly 
RM L50L18) 



ACOUSTIC ANALYSIS OF RAM-JET BUZZ. Harola 
Mirels. November 1955. 33p diagrs. 
(NACA TN 3574) 



(1.4. 1. 1) 
NOSE, CENTRAL. 

FLIGHT DETERMINATION OF DRAG OF NORMAL - 
SHOCK NOSE INLETS WITH VARIOUS COWLING 
PROFILES AT MACH NUMBERS FROM 0.9 TO 1.5. 
R. I. Sears, C. F. Merlet, and L. W. Putland. 
October 1953. 36p. diagrs., photos., tabs. (NACA 
RM L53I25a) 



THEORETICAL AND EXPERIMENTAL ANALYSIS 
OF LOW -DRAG SUPERSONIC INLETS HAVING A 
CIRCULAR CROSS SECTION AND A CENTRAL 
BODY AT MACH NUMBERS OF 3. 30, 2. 75, AND 
2.45. Antonio Ferri and Louis M. Nucci. 1954. 
ii, 37p. diagrs., photos. (NACA Rept. 1189. 
Supersedes RM L8H13) 



SOME INTERNAL -FLOW CHARACTERISTICS OF 
SEVERAL AXISYMMETRICAL NACA 1 -SERIES 
NOSE AIR INLETS AT ZERO FLIGHT SPEED. 
Carroll R. Bryan and Frank F. Fleming. July 1954. 
30p. diagrs., photos. (NACA RM L54E19a) 



AMPLITUDE OF SUPERSONIC DIFFUSER FLOW 
PULSATIONS. William H. Sterbentz and Joseph 
Davids. October 1955. 23p. diagrs; 
(NACA TN 3572. Supersedes RM E52I24) 



(1.4. 1. 1. 1) 

Propeller -Spinner - Cowl 

Combinations 

AN INVESTIGATION OF A FOUR-BLADE SINGLE- 
ROTATION PROPELLER IN COMBINATION WITH 
AN NACA 1 -SERIES D-TYPE COWLING AT MACH 
NUMBERS UP TO 0.83. Robert M. Reynolds, 
Robert I. Sammonds, and George C. Kenyon. 
April 1953. 71p. diagrs., photos. 
(NACA RM A53B06) 



59 



(1) AERODYNAMICS 



PRELIMINARY RESULTS OF AN INVESTIGATION 
OF THE EFFECTS OF SPINNER SHAPE ON THE 
CHARACTERISTICS OF AN NACA D-TYPE COWL 
BEHIND A THREE-BLADE PROPELLER, IN- 
CLUDING THE CHARACTERISTICS OF THE PRO- 
PELLER AT NEGATIVE THRUST. Robert M. 
Reynolds. November 1953. 15p. diagrs., photo., 
tab. (NACA RM A53J02) 



EFFECTS OF TWO SPINNER SHAPES ON THE 
PRESSURE RECOVERY IN AN NACA 1-SERIES 
D-TYPE COWL BEHIND A THREE-BLADE PRO- 
PELLER AT MACH NUMBERS UP TO 0.80. Ashley 
J. Molk and Robert M. Reynolds. March 1954. 
34p. diagrs., photo., tab. (NACA RM A53L29a) 



INVESTIGATION OF A THREE-BLADE PROPELLER 
IN COMBINATION WITH TWO DIFFERENT 
SPINNERS AND AN NACA D-TYPE COWL AT MACH 
NUMBERS UP TO 0,80. George C. Kenyon and 
Robert M. Reynolds. April 1954. 62p. diagrs., 
photos., tab. (NACA RM A54B18a) 



(1.4. 1. 1.2) 

Subsonic 

PERFORMANCE OF AIR INLETS AT TRANSONIC 
AND LOW SUPERSONIC SPEEDS. Mark R. Nichols 
and Robert E. Pendley. February 1952. 22p. 
diagrs. (NACA RM L52A07) 



(1.4. 1.1.3) 

Supersonic 

CHARACTERISTICS OF FOUR NOSE INLETS AS 
MEASURED AT MACH NUMBERS BETWEEN 1.4 
AND 2.0. George B. Brajnikoff and Arthur W, 
Rogers. June 25, 1951. 48p. diagrs., photos. 
(NACARM A51C12) 



PERFORMANCE OF AIR INLETS AT TRANSONIC 
AND LOW SUPERSONIC SPEEDS. Mark R. Nichols 
and Robert E. Pendley. February 1952. 22p. 
diagrs. (NACA RM L52A07) 



SOME INTERNAL-FLOW CHARACTERISTICS AT 
ZERO FLIGHT SPEED OF AN ANNULAR SUPER- 
SONIC INLET AND AN OPEN-NOSE INLET WITH 
SHARP AND ROUNDED LIPS. Joseph R. MiLillo. 
July 1954. 23p. diagrs., photo. 
(NACA RM L54E19) 



(1.4.1.2) 
NOSE, ANNULAR 

PRELIMINARY INVESTIGATION OF HELMHOLTZ 
RESONATORS FOR DAMPING PRESSURE FLUCTU- 
ATIONS IN 3.6-INCH RAM JET AT MACH NUMBER 
1.90. Jerome L. Fox. May 22, 1951. 24p. diagrs., 
photos. (NACA RM E51C05) 



CHARACTERISTICS OF FOUR NOSE INLETS AS 
MEASURED AT MACH NUMBERS BETWEEN 1.4 
AND 2.0. George B. Brajnikoff and Arthur W. 
Rogers. June 25, 1951. 48p. diagrs., photos. 
(NACARM A51C12) 



PERFORMANCE OF AIR INLETS AT TRANSONIC 
AND LOW SUPERSONIC SPEEDS. Mark R. Nichols 
and Robert E. Pendley. February 1952. 22p. 
diagrs. (NACA RM L52A07) 



EFFECTS OF TWO SPINNER SHAPES ON THE 
PRESSURE RECOVERY IN AN NACA 1-SERIES 
D-TYPE COWL BEHIND A THREE-BLADE PRO- 
PELLER AT MACH NUMBERS UP TO 0.80. Ashley 
J. Molk and Robert M. Reynolds. March 1954. 
34p. diagrs., photo., tab. (NACA RM A53L29a) 



SOME INTERNAL -FLOW CHARACTERISTICS OF 
SEVERAL AXISYMMETRICAL NACA 1-SERIES 
NOSE AIR INLETS AT ZERO FLIGHT SPEED. 
Carroll R. Bryan and Frank F. Fleming. July 1954. 
30p. diagrs., photos. (NACA RM L54E19a) 



ESTIMATION OF INLET LD? FORCES AT SUBSONIC 
AND SUPERSONIC SPEEDS. W. E. Moeckel. June 
1955. 12p. diagrs. (NACA TN 3457) 



DESIGN CRITERIA FOR AXISYMMETRIC AND TWO- 
PIMENSIONAL SUPERSONIC INLETS AND EXITS. 
James F. Connors and Rudolph C. Meyer. 
January 1956. 42p. diagrs., tabs. (NACA TN 3589) 



(1.4. 1.3) 
WING LEADING EDGE 

ALTITUDE INVESTIGATION OF PERFORMANCE OF 
TURBINE-PROPELLER ENGINE AND ITS COMPO- 
NENTS. Lewis E. Wallner and Martin J. Saari. 
October 5, 1950. 65p. diagrs., photos. (NACA 
RM E50H30) 



PERFORMANCE OF AIR INLETS AT TRANSONIC 
AND LOW SUPERSONIC SPEEDS. Mark R. Nichols 
and Robert E, Pendley. February 1952. 22p. 
diagrs. (NACA RM L52A07) 



(1.4. 1.4) 

SIDE 

PRELIMINARY DATA ON THE EFFECT OF BODY- 
NOSE BLUNTNESS ON THE DRAG AND PRESSURE 
RECOVERY OF A SIDE-INLET-BODY COMBINA- 
TION AT MACH NUMBERS OF 1.4 AND 1.7. 
John F. Stroud and Warren E. Anderson. April 25, 
1951. 13p. diagrs., photos. (NACA RM A51A09) 



DESIGN CRITERIA FOR AXISYMMETRIC AND TWO- 
DIMENSIONAL SUPERSONIC INLETS AND EXITS. 
James F. Connors and Rudolph C. Meyer. 
January 1956. 42p. diagrs., tabs. (NACA TN 3589) 



(1.4. 1.4. 1) 
Scoops 

EXPERIMENTAL INVESTIGATION AT SUPERSONIC 
SPEEDS OF TWIN-SCOOP DUCT INLETS OF EQUAL 
AREA. I. - AN INLET ENCLOSING 61.5 PERCENT 
OF THE MAXIMUM CIRCUMFERENCE OF THE 
FOREBODY. Wallace F. Davis and David L. 
Goldstein. January 21, 1948. 16p. diagrs., photos. 
(NACA RM A7J27) 



60 



(1) AERODYNAMICS 



EXPERIMENTAL INVESTIGATION AT SUPERSONIC 
SPEEDS OF TWIN-SCOOP DUCT INLETS OF EQUAL 
AREA, n - EFFECTS OF SLOTS UPON AN INLET 
ENCLOSING 61.5 PERCENT OF THE MAXIMUM 
CIRCUMFERENCE OF THE FOREBQDY. Wallace F. 
Davis and David L. Goldstein. June 9, 1948. 15p. 
diagrs., photos. (NACA RM A8C11) 

EXPERIMENTAL INVESTIGATION AT SUPERSONIC 
SPEEDS OF TWIN-SCOOP DUCT INLETS OF EQUAL 
AREA. HI - INLET ENCLOSING 37.2 PERCENT OF 
THE MAXIMUM CIRCUMFERENCE OF THE FORE- 
BODY. Wallace F. Davis and Sherman S. Edwards. 
July 22, 1948. 25p. diagrs., photos. 
{NACA RM A8E04) 



EXPERIMENTAL INVESTIGATION AT SUPERSONIC 
SPEEDS OF TWIN-SCOOP DUCT INLETS OF EQUAL 
AREA. IV - SOME EFFECTS OF INTERNAL DUCT 
SHAPE UPON AN INLET ENCLOSING 37.2 PERCENT 
OF THE FOREBODY CIRCUMFERENCE. Wallace F. 
Davis, Sherman S. Edwards, and George B. 
Brajnikotf. March 15, 1949. 21p. diagrs., photos. 
(NACA RM A9A31) 

PRELIMINARY DATA ON THE EFFECT OF BODY- 
NOSE BLUNTNESS ON THE DRAG AND PRESSURE 
RECOVERY OF A SIDE-INLET-BODY COMBINA- 
TION AT MACH NUMBERS OF 1.4 AND 1.7. 
John F. Stroud and Warren E. Anderson. April 25, 
1951. 13p. diagrs., photos. {NACA RM A51A09) 



SOME LOW -SPEED CHARACTERISTICS OF AN 
AIR-INDUCTION SYSTEM HAVING SCOOP-TYPE 
INLETS WITH PROVISIONS FOR BOUNDARY- 
LAYER CONTROL. Earl C. Watson. August 1951. 
42p. diagrs., photos., tab. {NACA RM A51F15) 



PERFORMANCE OF AIR INLETS AT TRANSONIC 
AND LOW SUPERSONIC SPEEDS. Mark R. Nichols 
and Robert E. Pendley. February 1952. 22p. 
diagrs. (NACA RM L52A07) 



EXPERIMENTAL INVESTIGATION OF INTERNAL- 
FLOW CHARACTERISTICS OF FORWARD UNDER- 
SLUNG FUSELAGE SCOOPS WITH UNSWEPT AND 
SWEPTBACK ENTRANCE AT MACH NUMBERS OF 
1.41 TO 1.96. Robert W. Boswinkle, Jr., and 
Meade H. Mitchell, Jr. March 1952. 34p. photos., 
diagrs. (NACA RM L52A24) 



AN ANALYTICAL STUDY OF THE COMPARATIVE 
PERFORMANCE OF FOUR AIR-INDUCTION SYS- 
TEMS FOR TURBOJET-POWERED AIRPLANES 
DESIGNED TO OPERATE AT MACH NUMBERS UP 
TO 1.5. James R. Blackaby. June 1952. 38p. 
diagrs. (NACA RM A52C14) 



A FLIGHT COMPARISON OF A SUBMERGED INLET 
AND A SCOOP INLET AT TRANSONIC SPEEDS. 
L. Stewart Rolls. March 1953. 41p. diagrs., 
photo., tab. (NACA RM A53A06) 



PRESSURE AND FORCE CHARACTERISTICS AT 
TRANSONIC SPEEDS OF A SUBMERGED 
DIVERGENT- WALLED AIR INLET ON A BODY OF 
REVOLUTION. John A. Braden and P. Kenneth 
Pierpont. May 1953. 65p. photos., diagrs., tabs. 
(NACA RM L53C13) 



CHARTS OF BOUNDARY-LAYER MASS FLOW AND 
MOMENTUM FOR INLET PERFORMANCE ANALY- 
SIS MACH NUMBER RANGE, 0.2 TO 5.0. Paul C. 
Simon and Kenneth L. Kowalski. November 1955. 
32p. diagrs., tab. (NACA TN 3583) 

(1.4. 1.4.2) 

Submerged 

A FLIGHT COMPARISON OF A SUBMERGED INLET 
AND A SCOOP INLET AT TRANSONIC SPEEDS. 
L. Stewart Rolls. March 1953. 41p. diagrs., 
photo., tab. (NACA RM A53A06) 

PRESSURE AND FORCE CHARACTERISTICS AT 
TRANSONIC SPEEDS OF A SUBMERGED 
DIVERGENT-WALLED AIR INLET ON A BODY OF 
REVOLUTION. John A. Braden and P. Kenneth 
Pierpont. May 1953. 65p. photos., diagrs., tabs. 
(NACARML53C13) 



(1.4.2) 
DUCTS 

WIND-TUNNEL INVESTIGATION AT LOW SPEED 
OF EFFECT OF SIZE AND POSITION OF CLOSED 
AIR DUCTS ON STATIC LONGITUDINAL AND 
STATIC LATERAL STABILITY CHARACTERISTICS 
OF UNSWEPT -MIDWING MODELS HAVING WINGS 
OF ASPECT RATIO 2, 4, AND 6. Byron M. Jaquet 
and James L. Williams. September 1955. 45p. 
diagrs., photos., tabs. (NACA TN 3481) 

(1.4.2. 1) 
DIFFUSERS 

PRELIMINARY INVESTIGATION OF EFFECTS OF 
COMBUSTION IN RAM JET ON PERFORMANCE OF 
SUPERSONIC DIFFUSERS. I - SHOCK DIFFUSER 
WITH TRIPLE-SHOCK PROJECTING CONE. J. F. 
Connors and A. H. Schroeder. September 15, 1948. 
18p. diagrs. (NACA RM E8F15) 



PRELIMINARY INVESTIGATION OF EFFECTS OF 
COMBUSTION IN RAM JET ON PERFORMANCE OF 
SUPERSONIC DIFFUSERS. II - PERFORATED 
SUPERSONIC INLET. Albert H. Schroeder and 
James F. Connors. October 4, 1948. 14p. diagrs. 
(NACA RM E8G16) 



PRELIMINARY INVESTIGATION OF EFFECTS OF 
COMBUSTION IN RAM JET ON' PERFORMANCE OF 
SUPERSONIC DIFFUSERS. HI - NORMAL-SHOCK 
DIFFUSER. Albert H. Schroeder and James F. 
Connors. December 22, 1948, 15p. diagrs. 
(NACARME8J18) 



EXPERIMENTAL INVESTIGATION OF PRESSURE 
FLUCTUATIONS IN 3.6-INCH RAM JET AT MACH 
NUMBER 1.92. James F. Connors and Albert H. 
Schroeder. October 13, 1949. 20p. diagrs., photos. 
(NACA RM E9H12) 



THEORETICAL AND EXPERIMENTAL ANALYSIS 
OF LOW-DRAG SUPERSONIC INLETS HAVING A 
CIRCULAR CROSS SECTION AND A CENTRAL 
BODY AT MACH NUMBERS OF 3. 30, 2. 75, AND 
2.45. Antonio Ferri and Louis M. Nucci. 1954. 
ii, 37p. diagrs., photos. (NACA Rept. 1189. 
Supersedes RM L8H13) 



61 



(1) AERODYNAMICS 



FLIGHT DETERMINATION OF THE DRAG AND 
PRESSURE RECOVERY OF AN NACA 1-40-250 NOSE 
INLET AT MACH NUMBERS FROM 0.9 TO 1.8. 
R. I. Sears and C. F. Merlet. July i955. 3Qp. 
diagrs., photos., 2 tabs. (NACA TN 3218. Formerly 
RM L50L18) 



PRELIMINARY INVESTIGATION OF A FAMILY OF 
DIFFUSERS DESIGNED FOR NEAR SONIC INLET 
VELOCITIES. Richard Scherrer and Warren E. 
Anderson. February 1956. 43p. diagrs.. photo. 
(NACA TN 3668) 



(1.4.2. 1. 1) 
Subsonic 



SOME LOW-SPEED CHARACTERISTICS OF AN 
AIR-INDUCTION SYSTEM HAVING SCOOP-TYPE 
INLETS WITH PROVISIONS FOR BOUNDARY- 
LAYER CONTROL. Earl C. Watson. August 1951. 
42p. diagrs., photos., tab. (NACA RM A51F15) 



AN ANALYTICAL STUDY OF THE COMPARATIVE 
FJSKft-OKMAKcE OF FOUR AIR-INDUCTION SYS- 
TEMS FOR TURBOJET-POWERED AIRPLANES 
DESIGNED TO OPERATE AT MACH NUMBERS UP 
TO 1.5. James R. Blackaby. June 1952. 38p. 
diagrs. (NACA RM A52C14) 



FLOW DIFFUSION IN A CONSTANT-DIAMETER 
DUCT DOWNSTREAM OF AN ABRUPTLY TERMI- 
NATED CENTER BODY. Charles C. Wood and 
James T. Higginbotham. July 1953. 27p. diagrs. 
(NACA RM L53D23) 



THEORETICAL PERFORMANCE CHARACTERIS- 
TICS OF SHARP-LIP INLETS AT SUBSONIC 
SPEEDS. Evan A. Fradenburgh and DeMarquis D. 
Wyatt. 1954. ii, 8p. diagrs. (NACA Rept. 1193. 
Formerly TN 3004) 



PERFORMANCE AND BOUNDARY -LAYER DATA 
FROM 120 AND 2 3° CONICAL DIFFUSERS OF AREA 
RATIO 2.0 AT MACH NUMBERS UP TO CHOKING 
AND REYNOLDS NUMBERS UP TO 7.5 x 10*. 
B. H. Little, Jr., and Stafford W. Wilbur. 1954. 
ii, 23p. diagrs., tabs. (NACA Rept. 1201. Super- 
sedes RM L9H10; RM L9K10; RM L50C02a) 



PRELIMINARY INVESTIGATION OF THE FLOW IN 
AN ANNULAR-DIFFUSER— TAILPIPE COMBINA- 
TION WITH AN ABRUPT AREA EXPANSION AND 
SUCTION, INJECTION, AND VORTEX-GENERATOR 
FLOW CONTROLS. John R. Henry and Stafford W. 
Wilbur. February 1954. 27p. diagrs. 
(NACA RM L53K30) 



PRELIMINARY INVESTIGATION OF SHORT TWO- 
DIMENSIONAL SUBSONIC DIFFUSERS. Richard R, 
Woollett. May 1956. 19p. diagrs., photos., tab. 
(NACA RM E56C02) 



(1.4.2.1.2) 

Supersonic 



PRELIMINARY INVESTIGATION OF HELMHOLTZ 
RESONATORS FOR DAMPING PRESSURE FLUCTU- 
ATIONS IN 3.6-INCH RAM JET AT MACH NUMBER 
1.90. Jerome L. Fox. May 22, 1951. 24p. diagrs., 
photos. (NACA RM E51C05) 



CHARACTERISTICS OF FOUR NOSE INLETS AS 
MEASURED AT MACH NUMBERS BETWEEN 1.4 
AND 2.0. George B. Brajnikoff and Arthur W. 
Rogers. June 25, 1951. 48p. diagrs., photos. 
(NACARMA51C12) 



THEORETICAL PERFORMANCE CHARACTERIS- 
TICS OF SHARP-UP INLETS AT SUBSONIC 
SPEEDS. Evan A. Fradenburgh and DeMarquis D. 
Wyatt. 1954. ii, 8p. diagrs. (NACA Rept. 1193. 
Formerly TN 3004) 



SOME OBSERVATIONS OF SHOCK-INDUCED TUR- 
BULENT SEPARATION ON SUPERSONIC DIF- 
FUSERS. T. J. Nussdorfer. May 1954. 14p. 
diagrs., photos. (NACA RM E51L26) 



EXPLORATORY INVESTIGATION OF FLOW IN THE 
5EFARATED REGION AHEAD OF TWO BLUNT 
BODIES AT MACH NUMBER 2. Harry Bernstein 
and William E. Brunk. June 1955. 27p. diagrs., 
tkhotos. (NACA RM E55D07b) 



CRITERIONS FOR PREDICTION AND CONTROL OF 
RAM-JET FLOW PULSATIONS. William H. 
Sterbentz and John C. Eward. August 1955. 60p. 
diagrs., photos. (NACA TN 350G. Formerly 
RM E51C27) 



AMPLITUDE OF SUPERSONIC DIFFUSER FLOW 
PULSATIONS. William H. Sterbentz and Joseph 
Davids. October 1955. 23p. diagrs; 
(NACA TN 3572. Supersedes RM E52I24) 



ACOUSTIC ANALYSIS OF RAM-JET BUZZ. 
Mir els. November 1955. 33p diagrs. 
(NACA TN 3574) 



Harold 



INVESTIGATION OF THE EFFECT OF SHORT 
FDCED DIFFUSERS ON STARTING BLOWDOWN 
JETS IN THE MACH NUMBER RANGE FROM 2.7 
TO 4.5. John A. Moore. January 1956. 32p. 
diagrs., photos. (NACA TN 3545) 



DESIGN CRITERIA FOR AXISYMMETRIC AND TWO- 
DIMENSIONAL SUPERSONIC INLETS AND EXITS. 
James F. Connors and Rudolph C. Meyer. 
January 1956. 42p. diagrs., tabs. (NACA TN 3589) 



(1.4.2. 2) 
NOZZLES 

INVESTIGATION OF EFFECTS OF MOVABLE 
EXHAUST-NOZZLE PLUG ON OPERATIONAL PER- 
FORMANCE OF 20-INCH RAM JET. William H. 
Sterbentz and Fred A. Wilcox. July 27, 1948. 32p. 
diagrs., photos. (NACA RM E8D22) 



62 



(1) AERODYNAMICS 



AERODYNAMIC INVESTIGATION OF A PARABOLIC 
BODY OF REVOLUTION AT MACH NUMBER OF 
1.92 AND SOME EFFECTS OF AN ANNULAR JET 
EXHAUSTING FROM THE BASE. Eugene S. Love. 
February 8, 1950. 75p. diagrs., photos., tab. 
(NACA RM L9K09) 



PRELIMINARY INVESTIGATION OF A PERFO- 
RATED AXIALLY SYMMETRIC NOZZLE FOR 
VARYING NOZZLE PRESSURE RATIOS. Eli 
Reshotko. January 1953. 43p. diagrs., photo., 
2 tabs. (NACA RM E52J27) 



AN ANALYTICAL STUDY OF THE EFFECT OF 
AIRPLANE WAKE ON THE LATERAL DISPERSION 
OF AERIAL SPRAYS. Wilmer H. Reed, in. 1954. 
ii, 16p. diagrs., 3 tabs. {NACA Rept. 1196. 
Formerly TN 3032) 



(1,4.2. 3) 

PIPES 

AVERAGING OF PERIODIC PRESSURE PULSA- 
TIONS BY A TOTAL-PRESSURE PROBE. R. C. 

Johnson. October 1955. 30p. diagrs., photo., 
tabs. (NACA TN 3568) 



(1.4. 2.4) 
BENDS 

PRELIMINARY INVESTIGATION OF A FAMILY OF 
DIFFUSERS DESIGNED FOR NEAR SONIC INLET 
VELOCITIES. Richard Scherrer and Warren E. 
Anderson. February 1956 43p. diagrs., photo. 
(NACA TN 3668) 



A STUDY OF THE HIGH-SPEED PERFORMANCE 
CHARACTERISTICS OF 90° BENDS IN CIRCULAR 
DUCTS. James T. Hlgginbotham, Charles C. Wood, 
and E. Floyd Valentine. June 1956. 28p. diagrs. 
(NACA TN 3696) 



(1.4.3) 
EXITS 

INVESTIGATION AT MACH NUMBER 1.91 OF 
SPREADING CHARACTERISTICS OF JET EXPAND- 
ING FROM CHOKED NOZZLES. Morris D. Rousso 
and L. Eugene Baughman. February 1952. 27p. 
photos., diagrs. (NACA RM E51L19) 



PRELIMINARY INVESTIGATION OF A PERFO- 
RATED AXIALLY SYMMETRIC NOZZLE FOR 
VARYING NOZZLE PRESSURE RATIOS. Eli 
Reshotko. January 1953. 43p. diagrs.. photo., 
2 tabs. (NACA RM E52J27) 



PRELIMINARY INVESTIGATION OF SEVERAL 
TARGET-TYPE THRUST-REVERSAL DEVICES. 
FredW. Steffen, H. George Krull and Carl C. 
Ciepluch. March 1954. 43p. diagrs., tab. (NACA 
RM E53L15b) 



AN INVESTIGATION OF THE DISCHARGE AND 
DRAG CHARACTERISTICS OF AUXILIARY -AIR 
OUTLETS DISCHARGING INTO A TRANSONIC 
STREAM. Paul E. Dewey and Allen R. Vick. July 
1955. 38p. diagrs., photos. (NACA TN 3466) 

SUMMARY EVALUATION OF TOOTHED-NOZZLE 
ATTACHMENTS AS A JET -NOISE -SUPPRESSION 
DEVICE. Warren J. North. July 1955. 19p. 
diagrs., photo. (NACA TN 3516) 

PERFORMANCE CHARACTERISTICS OF HEMI- 
SPHERICAL TARGET-TYPE THRUST REVERSERS. 
FredW. Steffen, Jack G. McArdle, and James W, 
Coats. September 1955. 39p. diagrs., photos., 
tab. (NACA RM E55E18) 



EFFECT OF EXHAUST -NOZZLE EJECTORS ON 
TURBOJET NOISE GENERATION. Warren J. North 
and Willard D. Coles. October 1955. 26p. diagrs., 
photo. (NACA TN 3573) 

PERFORMANCE CHARACTERISTICS OF CYLIN- 
DRICAL TARGET -TYPE THRUST REVERSERS. 
Fred W. Steffen and Jack G. McArdle. January 
1956. 40p. diagrs., photo. (NACA RM E55I29) 



DESIGN CRITERIA FOR AXISYMMETRIC AND TWO- 
DIMENSIONAL SUPERSONIC INLETS AND EXITS. 
James F. Connors and Rudolph C. Meyer. 
January 1956. 42p. diagrs., tabs. (NACA TN 3589) 



INVESTIGATION OF FAR NOISE FIELD OF JETS. 

I - EFFECT OF NOZZLE SHAPE. Edmund E. 
Callaghan and Willard D. Coles. January 1956. 
44p. diagrs., photos. (NACA TN 3590) 

INVESTIGATION OF FAR NOISE FIELD OF JETS. 

II - COMPARISON OF AIR JETS AND JET ENGINES. 
Willard D. Coles and Edmund E. Callaghan. 
January 1956. 19p. diagrs., photos. 

(NACA TN 3591) 



SUMMARY OF SCALE-MODEL THRUST-REVERSER 
INVESTIGATION. John H. Povolny, FredW. 
Steffen, and Jack G. McArdle. February 1956. 
49p. diagrs., photos. (NACA TN 3664) 



(1.4.4) 

JET PUMPS AND 

THRUST AUGMENTORS 

PERFORMANCE CHARACTERISTICS OF AIRCRAFT 
COOLING EJECTORS HAVING SHORT CYLINDRICAL 
SHROUDS. Fred D. Kochondorfer and Morris D. 
Rousso. May 22, 1951. 39p. diagrs. 
(NACA RM E51E01) 

PRELIMINARY AIR-FLOW AND THRUST CALIBRA- 
TIONS OF SEVERAL CONICAL COOLING-AIR 
EJECTORS WITH A PRIMARY TO SECONDARY 
TEMPERATURE RATIO OF 1.0. I - DIAMETER 
RATIOS OF 1.21 AND 1.10. W. K. Greathouse ar 
D. P. HoLlister. July 1952. 24p. diagrs. 
(NACA RM E52E21) 



63 



(1) AERODYNAMICS 



PRELIMINARY AIR-FLOW AND THRUST CALIBRA- 
TIONS OF SEVERAL CONICAL COOLING-AIR 
EJECTORS WITH A PRIMARY TO SECONDARY 
TEMPERATURE RATIO OF 1.0. II - DIAMETER 
RATIOS OF 1.06 AND 1.40. W. K. Greathouse and 
D. P. Hollister. August 1952. 35p. diagrs. 
(NACA RM E52F26) 



EFFECT OF EXHAUST -NOZZLE EJECTORS ON 
TURBOJET NOISE GENERATION. Warren J. North 
and Willard D. Coles. October 1955. 26p. diagrs., 

photo. (NACA TN 3573) 



(1.4.5) 
CASCADES 



COMPARISON OF NACA 65 -SERIES COMPRESSOR- 
BLADE PRESSURE DISTRIBUTIONS AND PER- 
FORMANCE IN A ROTOR AND IN CASCADE. 
Willard R. Westphal and William R. Godwin. 
November 1951. 53p. diagrs., photos. 
(NACA RM L51H20) 



METHOD OF ESTIMATING THE INCOMPRESSIBLE- 
FLOW PRESSURE DISTRIBUTION OF COMPRESSOR 
BLADE SECTIONS AT DESIGN ANGLE OF ATTACK. 
John R. Erwin and Laura A. Yacobi. December 
1953. 41p. diagrs., tab. (NACA RM L53F17) 



PRELIMINARY PERFORMANCE DATA OF SEVERAL 
TAIL-PIPE-CASCADE-TYPE MODEL THRUST 
REVERSERS. James G. Hcnzel, Jr. and Jack G. 
McArdle. August 1955. 48p. diagrs., photo*., tab. 
(NACA RM E55F09) 



SUMMARY OF SCALE-MODEL THRUST- REVERSE R 
INVESTIGATION. John H. Povolny, FredW. 
Steffen, and Jack G. McArdle. February 1956. 
49p. diagrs., photos. (NACA TN 3664) 



FLOW OF GAS THROUGH TURBINE LATTICES. 
M. E. Deich. May 1956. 136p. diagrs., photos. 
(NACA TM 1393. Trans, of Russian book: 
Technical Gasdynamics, ch. 7, 1953, p. 312-420) 



(1.4.5.1) 
THEORY 

THEORETICAL ANALYSIS OF INCOMPRESSIBLE 
FLOW THROUGH A RADIAL-INLET CENTRIFUGAL 
IMPELLER AT VARIOUS WEIGHT FLOWS. I - 
SOLUTION BY A MATRIX METHOD AND COMPAR- 
ISON WITH AN APPROXIMATE METHOD. Vasily D. 
Prian, James J. Kramer and Chung-Hua Wu. June 
1955. 39p. diagrs., tab. (NACA TN 3448) 



THEORETICAL ANALYSIS OF INCOMPRESSIBLE 
FLOW THROUGH A RADIAL-INLET CENTRIFUGAL 
IMPELLER AT VARIOUS WEIGHT FLOWS. - 
SOLUTION IN LEADING-EDGE REGION BY RELAX 
ATION METHODS. James J. Kramer. June 1955. 
19p. diagrs. (NACA TN 3449) 



THEORETICAL LOSS RELATIONS FOR LOW- 
SPEED TWO-DIMENSIONAL -CASCADE FLOW. 
Seymour Lieblein and William H. Roudebush. 
March 1956. 46p. diagrs., tab. (NACA TN 3662) 



FLAT PLATE CASCADES AT SUPERSONIC SPEED. 
(Ebene Plattengitter bei Uberschallgeschwindigkeit). 
Rashad M. El Badrawy. May 1956. iii, 130p. 
diagrs., photos., tabs. (NACA TM 1369. Trans, of 
Eidgenbssische Technische Hochschule Zurich. 
Institut fiir Aerodynamic Mitteilungen 19) 



STALL PROPAGATION IN AXIAL-FLOW COM- 
PRESSORS. Alan H. Stenning, Anthony R. Kriebel, 
and Stephen R. Montgomery, Massachusetts Institute 
of Technology. June 1956. 83p. diagrs., photos., 
tab. (NACA TN 3580) 

(1.4. 5.2) 
EXPERIMENT 

TWO-DIMENSIONAL CASCADE INVESTIGATION OF 
THE MAXIMUM EXIT TANGENTIAL VELOCITY 
COMPONENT AND OTHER FLOW CONDITIONS AT 
THE EXIT OF SEVERAL TURBINE BLADE DESIGNS 
AT SUPERCRITICAL PRESSURE RATIOS. Cavour 
H. Hauser and Henry W. Plohr. August 1951. 34p. 
diagrs., photos. (NACA RM E51F12) 



SYSTEMATIC TWO-DIMENSIONAL CASCADE TESTS 
OF NACA 65 -SERIES COMPRESSOR BLADES AT 
LOW SPEEDS. L. Joseph Herrig, James C. Emerv 
and John R. Erwin. September 1951. 223p. 
diagrs., photo., tabs. (NACA RM L51G31) 



SOME EFFECTS OF BLADE TRAILING-EDGE 
THICKNESS ON PERFORMANCE OF A SINGLE- 
STAGE AXIAL-FLOW COMPRESSOR. J. J. Moses 
a«dG. K* Serovy, October 1951. 14p. diaers.. tab. 
(NACA RM E51F28) 



EFFECT OF SECTION THICKNESS AND TRAIUNG- 
EDGE RADIUS ON THE PERFORMANCE OF NACA 
65-SERIES COMPRESSOR BLADES IN CASCADE AT 
LOW SPEEDS. L. Joseph Herrig, James C. Emery, 
and John R. Erwin. December 1951. 66p. diagrs., 
tabs. (NACARML51J16) 



A COMPARISON OF TYPICAL NATIONAL GAS TUR- 
BINE ESTABLISHMENT AND NACA AXIAL-FLCW 
COMPRESSOR BLADE SECTIONS IN CASCADE AT 
LOW SPEED. A. Richard Felix and James C. 
Emery. May 1953. 46p. diagrs., photo., tabs. 
(NACA RM L53B26a) 



TWO-DIMENSIONAL LOW -SPEED CASCADE INVES- 
TIGATION OF NACA COMPRESSOR BLADE SEC- 
TIONS HAVING A SYSTEMATIC VARIATION IN 
MEAN-LINE LOADING. John R. Erwin, Melvyn 
Savage, and James C. Emery. November 1953. 
129p. diagrs., tabs. (NACA RM L53I30b) 



INVESTIGATION OF A RELATED SERIES OF 
TURBINE-BLADE PROFILES IN CASCADE. James 
C. Dunavant and John R. Er^in. December 1953. 
lOOp. diagrs. (NACA RM L53G15) 

SUMMARY OF 65-SERIES COMPRESSOR-BLADE 
LOW-SPEED CASCADE DATA BY USE OF THE 
CARPET-PLOTTING TECHNIQUE. A. Richard 
Felix. November 1954. 9p. diagrs. 
(NACA RM L54H18a) 



64 



(1) AERODYNAMICS 



EXPERIMENTAL INVESTIGATION OF BLADE 
FLUTTER IN AN ANNULAR CASCADE. J. R. Rowe 
and A. Mendelson. November 1955. 24p. diagrs., 
photos. (NACA TN 3581) 



STALL PROPAGATION IN AXIAL-FLOW COM- 
PRESSORS. Alan H. Stenning, Anthony R. Kriebel, 
and Stephen R. Montgomery, Massachusetts Institute 
of Technology. June 1956. 83p. diagrs., photos., 
tab, (NACA TN 3580) 



(1.4.6) 
FANS 



COMPARISON OF NACA 65-SERIES COMPRESSOR- 
BLADE PRESSURE DISTRIBUTIONS AND PER- 
FORMANCE IN A ROTOR AND IN CASCADE. 
Willard R. Westphal and William R. Godwin. 
November 1951. 53p. diagrs., photos. 
(NACA RM L51H20) 



(1.4.7) 
BOUNDARY LAYER 

FLOW DIFFUSION IN A CONSTANT-DIAMETER 
DUCT DOWNSTREAM OF AN ABRUPTLY TERMI- 
NATED CENTER BODY. Charles C. Wood and 
James T. Higginbotham. July 1953. 27p. diagrs. 
(NACA RM L53D23) 

PERFORMANCE AND BOUNDARY -LAYER DATA 
FROM 120 AND 23° CONICAL DIFFUSERS OF AREA 
RATIO 2.0 AT MACH NUMBERS UP TO CHOKING 
AND REYNOLDS NUMBERS UP TO 7.5 x 10 6 . 
B. H. Little, Jr., and Stafford W. Wilbur. 1954. 
ii, 23p. diagrs., tabs. (NACA Rept. 1201. Super- 
sedes RM L9H10; RM L9K10; RM L50C02a) 

SOME INTERNAL-FLOW CHARACTERISTICS OF 
SEVERAL AXISYMMETRICAL NACA 1 -SERIES 
NOSE AIR INLETS AT ZERO FLIGHT SPEED. 
Carroll R. Bryan and Frank F. Fleming. July 1954. 
30p. diagrs., photos. (NACA RM L54E19a) 

PRESSURE RISE ASSOCIATED WITH SHOCK- 
INDUCED BOUNDARY -LAYER SEPARATION. 
Eugene S. Love. December 1955. 32p. diagrs. 
(NACA TN 3601) 

CROSS FLOWS IN LAMINAR INCOMPRESSIBLE 
BOUNDARY LAYERS. Arthur G. Hansen and 
Howard Z. Herzig. February 1956. 50p. diagrs., 
photos., tabs. (NACA TN 3651) 



(1.4.7. 1) 

CHARACTERISTICS 

INTERSTAGE SURVEYS AND ANALYSIS OF VIS- 
COUS ACTION IN LATTER STAGES OF A MULTI- 
STAGE AXIAL-FLOW COMPRESSOR. William B. 
Briggs and Charles C. Giamati. March 1953. 51p. 
diagrs., photo., tab. (NACA RM E52I12) 

VISUALIZATION STUDY OF SECONDARY FLOWS 
IN TURBINE ROTOR TIP REGIONS. Hubert W. 
Allen and Milton G. Kofskey. September 1955. 
33p. diagrs., photos., tab. (NACA TN 3519) 



A SURVEY OF UNCLASSIFIED AXIAL-FLOW- 
COMPRESSOR LITERATURE. Howard Z. Herzig 
and Arthur G. Hansen. November 1955. i, 88p. 
(NACA RM E55H11) 

CHARTS OF BOUNDARY-LAYER MASS FLOW AND 
MOMENTUM FOR INLET PERFORMANCE ANALY- 
SIS MACH NUMBER RANGE, 0.2 TO 5.0. Paul C. 
Simon and Kenneth L. Kowalski. November 1955. 
32p. diagrs., tab. (NACA TN 3583) 

CROSS FLOWS IN LAMINAR INCOMPRESSIBLE 
BOUNDARY LAYERS. Arthur G. Hansen and 
Howard Z. Herzig. February 1956. 5 Op. diagrs., 
photos., tabs. (NACA TN 3651) 

PRELIMINARY INVESTIGATION OF A FAMILY OF 
DIFFUSERS DESIGNED FOR NEAR SONIC INLET 
VELOCITIES. Richard Scherrer and Warren E. 
Anderson. February 1956. 43p. diagrs., photo. 
(NACA TN 3668) 

FLOW OF GAS THROUGH TURBINE LATTICES. 
M. E. Deich. May 1956. 136p. diagrs., photos. 
(NACA TM 1393. Trans, of Russian book: 
Technical Gasdynamics, ch. 7, 1953, p. 312-420) 

PRELIMINARY REPORT ON A STUDY OF SEPA- 
RATED FLOWS IN SUPERSONIC AND SUBSONIC 
STREAMS. Dean R. Chapman, Donald M. Kuehn, 
and Howard K. Larson. June 1956. 15p. diagrs., 
photos. (NACA RM A55L14) 



(1,4.7.2) 
CONTROL 

SOME LOW-SPEED CHARACTERISTICS OF AN 
AIR-INDUCTION SYSTEM HAVING SCOOP-TYPE 
INLETS WITH PROVISIONS FOR BOUNDARY- 
LAYER CONTROL. Earl C. Watson. August 1951. 
42p. diagrs., photos., tab. (NACA RM A51F15) 

A FLIGHT COMPARISON OF A SUBMERGED INLET 
AND A SCOOP INLET AT TRANSONIC SPEEDS. 
L. Stewart Rolls. March 1953. 41p. diagrs., 
photo., tab. (NACA RM A53A06) 

PRELIMINARY INVESTIGATION OF THE FLOW IN 
AN ANNULAR-DIFFUSER— TAILPIPE COMBINA- 
TION WITH AN ABRUPT AREA EXPANSION AND 
SUCTION, INJECTION, AND VORTEX-GENERATOR 
FLOW CONTROLS. John R. Henry and Stafford W. 
Wilbur. February 1954. 27p. diagrs. 
(NACA RM L53K30) 

SOME OBSERVATIONS OF SHOCK-INDUCED TUR- 
BULENT SEPARATION ON SUPERSONIC DIF- 
FUSERS. T. J. Nussdorfer. May 1954. 14p. 
diagrs., photos. (NACA RM E51L26) 

CHARTS OF BOUNDARY-LAYER MASS FLOW AND 
MOMENTUM FOR INLET PERFORMANCE ANALY- 
SIS MACH NUMBER RANGE, 0,2 TO 5.0. Paul C. 
Simon and Kenneth L. Kowalski. November 1955. 
32p. diagrs., tab. (NACA TN 3583) 

ON THE PERMEABILITY OF POROUS MATERIALS. 
E. Carson Yates, Jr. January 1956. 31p. diagrs. 
(NACA TN 3596) 

PERFORATED SHEETS AS A POROUS MATERIAL 
FOR DISTRIBUTED SUCTION AND INJECTION. 
Robert E. Dannenberg, Bruno J. Gambucci, and 
James A. Weiberg. April 1956. 27p. diagrs., 
photos. (NACA TN 3669) 



65 



( 1 ) AERODYNAMICS 



(1.5) 
Propellers 



(1.5.1) 
THEORY 



A THEORETICAL STUDY OF THE EFFECT OF 
FORWARD SPEED ON THE FREE-SPACE SOUND- 
PRESSURE FIELD AROUND PROPELLERS. I. E 
Garrick and Charles E. Watkins. 1954. ii, 16p. 
diagrs., tab. (NACA Rept. 1198. Supersedes 
TN 3018) 



EXPERIMENTAL AND CALCULATED STATIC 
CHARACTERISTICS OF A TWO-BLADE NACA 
10-(3)(062)-045 PROPELLER. John M. Swihart. 
March 1954. 20p. diagrs., photos., tab. 
(NACA RM L54A19) 



(1.5.2) 
DESIGN VARIABLES 

FLUTTER OF THIN PROPELLER BLADES, 
INCLUDING EFFECTS OF MACH NUMBER, 
STRUCTURAL DAMPING, AND VIBRATORY- STRESS 
MEASUREMENTS NEAR THE FLUTTER 
BOUNDARIES. Harvey H. Hubbard, Marvin F. 
Burgess, and Maurice A. Sylvester. June 1956. 
25p. diagrs., tab. (NACA TN 3707) 



(1. 5.2. 1) 
BLADE SECTIONS 

THE EFFECT OF BLADE-SECTION CAMBER ON 
THE STALL-FLUTTER CHARACTERISTICS OF 
THREE NACA PROPELLERS AT ZERO ADVANCE. 
Arthur E. Allis and John M. Swihart. April 1953. 
29p. diagrs., photo., tab. (NACA RM L53B17) 



(1.5.2.2) 
SOLIDITY 

INVESTIGATION OF THE NACA 4-(5)(05)-O37 SIX- 
AND EIGHT-BLADE, DUAL-ROTATION PROPEL- 
LERS AT POSITIVE AND NEGATIVE THRUST AT 
MACH NUMBERS UP TO 0.90, INCLUDING SOME 
AERODYNAMIC CHARACTERISTICS OF THE NACA 
4-(5)(05)-041 TWO- AND FOUR-BLADE, SINGLE- 
ROTATION PROPELLERS. John H. Walker and 
Robert M. Reynolds. October 1954. 148p. diagrs., 
photos., tabs. (NACA RM A54G13) 



(1.5.2.5) 
MACH NUMBER EFFECTS 

AN INVESTIGATION OF A FOUR-BLADE SINGLE- 
ROTATION PROPELLER IN COMBINATION WITH 
AN NACA 1-SERIES D-TYPE COWLING AT MACH 
NUMBERS UP TO 0.83. Robert M. Reynolds, 
Robert I. Sammonds, and George C. Kenyon. 
April 1953. 71p. diagrs., photos. 
(NACA RMA53B06) 



PRELIMINARY RESULTS OF AN INVESTIGATION 
OF THE EFFECTS OF SPINNER SHAPE ON THE 
CHARACTERISTICS OF AN NACA D-TYPE COWL 
BEHIND A THREE-BLADE PROPELLER, IN- 
CLUDING THE CHARACTERISTICS OF THE PRO- 
PELLER AT NEGATIVE THRUST. Robert M. 
Reynolds. November 1953. 15p. diagrs., photo., 
tab. {NACA RM A53J02) 



A THEORETICAL STUDY OF THE EFFECT OF 
FORWARD SPEED ON THE FREE-SPACE SQUND- 
PRESSURE FIELD AROUND PROPELLERS. I. E. 
Garrick and Charles E. Watkins. 1954. ii, 16p. 
diagrs., tab. (NACA Rept. 1198. Supersedes 
TN 3018) 



EXPERIMENTAL AND CALCULATED STATIC 
CHARACTERISTICS OF A TWO- BLADE NACA 
10-(3)(062)-045 PROPELLER. John M. Swihart. 
March 1954. 2 Op. diagrs., photos., tab. 
(NACA RM L54A19) 



INVESTIGATION OF A THREE-BLADE PROPELLER 
IN COMBINATION WITH TWO DIFFERENT 
SPINNERS AND AN NACA D-TYPE COWL AT MACH 
NUMBERS UP TO 0.80. George C. Kenyon and 
Robert M. Reynolds. April 1954. 62p. diagrs., 
photos., tab. (NACA RM A54B18a) 



INVESTIGATION OF THE NACA 4-l5}(05)-037 SIX- 
AND EIGHT-BLADE, DUAL-ROTATION PROPEL- 
LERS AT POSITIVE AND NEGATIVE THRUST AT 
MACH NUMBERS UP TO 0.90, INCLUDING SOME 
AERODYNAMIC CHARACTERISTICS OF THE NACA 
4-(5)(05)-041 TWO- AND FOUR-BLADE, SINGLE- 
ROTATION PROPELLERS. John H. Walker and 
Robert M. Reynolds. October 1954. 148p. diagrs., 
photos., tabs. (NACA RM A54G13) 



ON THE GAS DYNAMICS OF A ROTATING IMPEL- 
LER. (Zur Gasdynamik des drehenden 
Schtufelsterns). A. Busemann. March 1956. 
16p. diagrs. (NACA TM 1385. Trans, from 
Zeitichrift fiir angewandte Mathematik und Mechanlk, 
v. 18, no. 1, February 1938, p. 31-38) 



(1.5.2.7) 
DUAL ROTATION 



DYNAMIC INVESTIGATION OF TURBINE - 
PROPELLER ENGINE UNDER ALTITUDE CONDI- 
TIONS. Richard P. Krebs, Seymour C. Himmel, 
Darnold Blivas, and Harold Shames. December 6, 
1950. 55p diagrs., photo. (NACA RM E50J24) 



DYNAMIC STABILITY AND CONTROL CHARACTER- 
ISTICS OF A VERTICALLY RISING AIRPLANE 
MODEL IN HOVERING FLIGHT. William R. Bates, 
Powell M. Lovell, Jr., and Charles C. Smith, Jr. 
February 23, 1951. 16p. diagrs., photos., tab. 
(NACA RM L50J16) 



66 



( 1 ) AERODYNAMICS 



EFFECT OF THE PROXIMITY OF THE GROUND ON 
THE STABILITY AND CONTROL CHARACTERIS- 
TICS OF A VERTICALLY RISING AIRPLANE MODEL 
IN THE HOVERING CONDITION. Charles C. Smith, 
Jr., Powell M. Lovell, Jr., and William R. Bates. 
September 1951. 16p. diagrs., tab. (NACA 
RML51G05) 



ADDITIONAL STUDIES OF THE STABILITY AND 
CONTROLLABILITY OF AN UNSWEPT-WING 
VERTICALLY RISING AIRPLANE MODEL IN 
HOVERING FLIGHT INCLUDING STUDIES OF VAR- 
IOUS TETHERED LANDING TECHNIQUES. 
William R. Bates, Powell M. Lovell, Jr., and 
Charles C. Smith, Jr. Movember 1951. 25p. 
diagrs., photos., tab. (NACA RM L5 1107a) 



INVESTIGATION OF THE NACA 4-(5)(05)-037 SDC- 
AND EIGHT-BLADE, DUAL-ROTATION PROPEL- 
LERS AT POSITIVE AND NEGATIVE THRUST AT 
MACH NUMBERS UP TO 0.90, INCLUDING SOME 
AERODYNAMIC CHARACTERISTICS OF THE NACA 
4-(5)(05)-041 TWO- AND FOUR-BLADE, SINGLE- 
ROTATION PROPELLERS. John H. Walker and 
Robert M. Reynolds. October 1954. 148p. diagrs., 
photos., tabs. (NACA RM A54G13) 



VIBRATORY-STRESS INVESTIGATION OF SDC- 
AND EIGHT-BLADE DUAL-ROTATING PROPEL- 
LERS OPERATING AT ZERO ADVANCE. Atwood R. 
Heath, Jr. and Robert L. O'Neal. February 1955. 
26p. diagrs., photo., tabs. (NACA RM L54J28) 



VELOCITY DISTRIBUTIONS MEASURED IN THE 
SLIPSTREAM OF EIGHT -BLADE AND SK -BLADE 
DUAL-ROTATING PROPELLERS AT ZERO 
ADVANCE. Leland B. Salters, Jr. June 1955. 
27p. diagrs., photo. (NACA RM L55D21) 



(1. 5.2.8) 
INTERFERENCE OF BODIES 



THE EFFECTS OF COMPRESSIBILITY ON THE 
UPWASH AT THE PROPELLER PLANES OF A 
FOUR-ENGINE TRACTOR AIRPLANE CONFIGURA- 
TION HAVING A WING WITH 40° OF SWEEPBACK 
AND AN ASPECT RATIO. OF 10. Armando E. 
Lopez and Jerald K. Dickson. April 1953. 38p. 
diagrs., photos., tab. (NACA RM A53A30a) 



AN INVESTIGATION OF A FOUR -BLADE SINGLE - 
ROTATION PROPELLER IN COMBINATION WITH 
AN NACA 1-SERIES D-TYPE COWLING AT MACH 
NUMBERS UP TO 0.83. Robert M. Reynolds, 
Robert I. Sammonds, and George C. Kenyon. 
April 1953. 71p. diagrs., photos. 
(NACA RM A53B06) 



PRELIMINARY RESULTS OF AN INVESTIGATION 
OF THE EFFECTS OF SPINNER SHAPE ON THE 
CHARACTERISTICS OF AN NACA D-TYPE COWL 
BEHIND A THREE-BLADE PROPELLER, IN- 
CLUDING THE CHARACTERISTICS OF THE PRO- 
PELLER AT NEGATIVE THRUST. Robert M. 
Reynolds. November 1953. 15p. diagrs., photo., 
tab. (NACA RM A53J02) 



INVESTIGATION OF A THREE-BLADE PROPELLER 
IN COMBINATION WITH TWO DIFFERENT 
SPINNERS AND AN NACA D-TYPE COWL AT MACH 
NUMBERS UP TO 0.80. George C. Kenyon and 
Robert M. Reynolds. April 1954. 62p. diagrs., 
photos., tab. (NACA RM A54B18a) 



(1.5.2.9) 
PITCH AND YAW 



A WIND-TUNNEL INVESTIGATION OF THE EF- 
FECTS OF THRUST-AXIS INCLINATION ON PRO- 
PELLER FIRST -ORDER VIBRATION. W. H. Gray, 
J. M. Hallissy, Jr., and A. R. Heath, Jr. 1954. 
ii, 37p. diagrs., photo., tab. (NACA Rept. 1205. 
Supersedes RM L SOD 13) 



AERODYNAMIC CHARACTERISTICS OF A SMALL- 
SCALE SHROUDED PROPELLER AT ANGLES OF 
ATTACK FROM 0° TO 90°. Lysle P. Parlett. 
November 1955. 12p. diagrs. (NACA TN 3547) 



(1.5.3) 
DESIGNATED TYPES 



AN INVESTIGATION OF A FOUR -BLADE SINGLE - 
ROTATION PROPELLER IN COMBINATION WITH 
AN NACA 1-SERIES D-TYPE COWLING AT MACH 
NUMBERS UP TO 0.83. Robert M. Reynolds, 
Robert I. Sammonds, and George C. Kenyon. 
April 1953. 71p. diagrs., photos. 
(NACA RM A53B06) 



INVESTIGATION OF A THREE-BLADE PROPELLER 
IN COMBINATION WITH TWO DIFFERENT 
SPINNERS AND AN NACA D-TYPE COWL AT MACH 
NUMBERS UP TO 0.80. George C. Kenyon and 
Robert M. Reynolds. April 1954. 62p. diagrs., 
photos., tab. (NACA RM A54B18a) 



INVESTIGATION OF THE NACA 4-(5)(05)-037 SLX- 
AND EIGHT-BLADE, DUAL-ROTATION PROPEL- 
LERS AT POSITIVE AND NEGATIVE THRUST AT 
MACH NUMBERS UP TO 0.90, INCLUDING SOME 
AERODYNAMIC CHARACTERISTICS OF THE NACA 
4-(5)(05)-041 TWO- AND FOUR-BLADE, SINGLE- 
ROTATION PROPELLERS. John H. Walker and 
Robert M. Reynolds. October 1954. 148p. diagrs., 
photos., tabs. (NACA RM A54G13) 



67 



(1) AERODYNAMICS 



FLAT PLATE CASCADES AT SUPERSONIC SPEED 
(Ebene Plattengitter bei Uberschallgeschwindigkeit) 
Rashad M. El Badrawy. May 1956. iii, 130p. 
diagrs., photos., tabs. (NACA TM 1369. Trans, of 
Eidgenossische Technische Hochschule Zurich. 
Institut fiir Aerodynamik. Mitteilungen 19) 



(1.5.4) 
SLIPSTREAM 



EFFECT OF THE PROXIMITY OF THE GROUND ON 
THE STABILITY AND CONTROL CHARACTERIS- 
TICS OF A VERTICALLY RISING AIRPLANE MODEL 
IN THE HOVERING CONDITION. Charles C. Smith 
Jr., Powell M. Lovell, Jr., and William R. Bates 
September 1951. 16p. diagrs., tab. (NACA 
RML51G05) 



EFFECTS OF OPERATING PROPELLERS ON THE 
WING-SURFACE PRESSURES OF A FOUR-ENGINE 
TRACTOR AIRPLANE CONFIGURATION HAVING A 
WING WITH 40° OF SWEEPBACK. Carl D. Kolbe 
and Frederick W. Boltz. April 1954. 133p. 
diagrs., photo., 19 tabs. (NACA RM A53L29) 



ANALYSIS OF WIND-TUNNEL TESTS AT LOW 
SPEEDS OF A FOUR-ENGINE PROPELLER- 
DRIVEN AIRPLANE CONFIGURATION HAVING A 
WING WITH 40° OF SWEEPBACK. George G. 
Edwards and Donald A. Buell. October 1954. 137p 
diagrs., photos., 2 tabs. (NACA RM A54F14) 



VELOCITY DISTRIBUTIONS MEASURED IN THE 
SLIPSTREAM OF EIGHT -BLADE AND SDC -BLADE 
DUAL-ROTATING PROPELLERS AT ZERO 
ADVANCE. Leland B. Salters, Jr. June 1955. 
27p. diagrs., photo. (NACA RM L55D21) 



INVESTIGATION OF THE EFFECTS OF GROUND 
PROXIMITY AND PROPELLER POSITION ON THE 
EFFECTIVENESS OF A WING WITH LARGE-CHORD 
SLOTTED FLAPS IN REDIRECTING PROPELLER 
SLIPSTREAMS DOWNWARD FOR VERTICAL TAKE- 
OFF. Richard E. Kuhn. March 1956. 38p. 
diagrs., photos., tab. (NACA TN 3629) 



INVESTIGATION AT ZERO FORWARD SPEED OF A 
LEADING-EDGE SLAT AS A LONGITUDINAL CON- 
TROL DEVICE FOR VERTICALLY RISING AIR- 
PLANES THAT UTILIZE THE REDIRECTED- 
SLIPSTREAM PRINCIPLE. Richard E. Kuhn. 
May 1956. 33p. diagrs., photos. (NACA TN 3692) 



PRELIMINARY INVESTIGATION OF THE EFFEC- 
TIVENESS OF A SLIDING FLAP IN DEFLECTING A 
PROPELLER SLIPSTREAM DOWNWARD FOR 
VERTICAL TAKE-OFF. Richard E. Kuhn and 
Kenneth P. Spreemann. May 1956. 25p. diagrs. 
photo. (NACA TN 3693) 



(1.5.6) 
OPERATING CONDITIONS 

THE EFFECTS OF COMPRESSIBILITY ON THE 
UPWASH AT THE PROPELLER PLANES OF A 
FOUR-ENGINE TRACTOR AIRPLANE CONFIGURA- 
TION HAVING A WING WITH 40° OF SWEEPBACK 
AND AN ASPECT RATIO.OF 10. Armando E. 
Lopez and Jerald K. Dickson. April 1953 38p 
diagrs., photos., tab. (NACA RM A53A30a) 



THE EFFECT OF BLADE-SECTION CAMBER ON 
THE STALL-FLUTTER CHARACTERISTICS OF 
THREE NACA PROPELLERS AT ZERO ADVANCE. 
Arthur E. Allts and John M. Swihart. April 1953. 
29p. diagrs., photo., tab. (NACA RM L53B17) 



EXPERIMENTAL AND CALCULATED STATIC 
CHARACTERISTICS OF A TWO-BLADE NACA 
10-(3)(062)-045 PROPELLER. John M. Swihart. 
March 1954. 20p. diagrs., photos., tab. (NACA 
RM L54A19) 



FLUTTER OF THIN PROPELLER BLADES 
INCLUDING EFFECTS OF MACH NUMBEr! 
STRUCTURAL DAMPING, AND VIBRATORY-STRESS 
MEASUREMENTS NEAR THE FLUTTER 
BOUNDARIES. Harvey H. Hubbard, Marvin F. 
Burgess, and Maurice A. Sylvester. June 1956 
25p. diagrs., tab. (NACA TN 3707) 

(1.5.7) 
PROPELLER - SPINNER - COWL 



COMBINATIONS 



AN INVESTIGATION OF A FOUR-BLADE SINGLE- 
ROTATION PROPELLER IN COMBINATION WITH 
AN NACA 1-SERIES D-TYPE COWLING AT MACH 
NUMBERS UP TO 0.83. Robert M. Reynolds, 
Robert I. Sammonds, and George C. Kenyon. 
April 1953. 71p, diagrs., photos. 
(NACA RM A53B06) 



PRELIMINARY RESULTS OF AN INVESTIGATION 
OF THE EFFECTS OF SPINNER SHAPE ON THE 
CHARACTERISTICS OF AN NACA D-TYPE COWL 
BEHIND A THREE-BLADE PROPELLER IN- 
CLUDING THE CHARACTERISTICS OF THE PRO- 
PELLER AT NEGATIVE THRUST. Robert M 
Reynolds. November 1953. 15p. diagrs., photo 
tab. (NACA RM A53J02) 



EFFECTS OF TWO SPINNER SHAPES ON THE 
PRESSURE RECOVERY IN AN NACA 1-SERIES 
D-TYPE COWL BEHIND A THREE-BLADE PRO- 
PELLER AT MACH NUMBERS UP TO 0.80. Ashley 
J. Molk and Robert M. Reynolds. March 1954. 
34p. diagrs., photo., tab. (NACA RM A53L29a) 



INVESTIGATION OF A THREE-BLADE PROPELLER 
IN COMBINATION WITH TWO DIFFERENT 
SPINNERS AND AN NACA D-TYPE COWL AT MACH 
NUMBERS UP TO 0.80. George C. Kenyon and 
Robert M. Reynolds. April 1954. 62p. diagrs 
photos., tab. (NACA RM A54B18a) 



68 



( 1 ) AERODYNAMICS 



(1.6) 
Rotating Wings 



(1.6.1) 
THEORY 



THE NORMAL COMPONENT OF THE INDUCED 
VELOCITY IN THE VICINITY OF A LIFTING ROTOR 
AND SOME EXAMPLES OF ITS APPLICATION. 
Walter Castles, Jr. and Jacob Henri De Leeuw, 
Georgia Institute of Technology. 1954. ii, 15p. 
diagrs., 3 tabs. (NACA Rept. 1184. Formerly 
TN 2912) 

CHARTS FOR ESTIMATING TAIL-ROTOR CONTRI- 
BUTION TO HELICOPTER DIRECTIONAL STABIL- 
ITY AND CONTROL IN LOW-SPEED FLIGHT. 
Kenneth B. Amer and Alfred Gessow. 1955. ii, 
22p. diagrs., photo., tabs.* (NACA Rept. 1216. 
Supersedes TN 3156) 

SUPPLEMENTARY CHARTS FOR ESTIMATING 
PERFORMANCE OF HIGH-PERFORMANCE HELI- 
COPTERS. Robert J. Tapscott and Alfred Gessow. 
July 1955. 31p. diagrs. (NaCA TN 3482) 

CHARTS FOR ESTIMATING ROTOR-BLADE FLAP- 
PING MOTION OF HIGH-PERFORMANCE HELICOP- 
TERS. Robert J. Tapscott and Alfred Gessow. 
March 1956. 19p. diagrs. (NACA TN 3616) 

NORMAL COMPONENT OF INDUCED VELOCITY IN 
THE VICINITY OF A LIFTING ROTOR WITH A NON- 
UNIFORM DISK LOADING. Harry H. Heyson and 
S. Katzoff. April 1956. i, 45p. diagrs. 
(NACA TN 3690) 

ANALYSIS AND COMPARISON WITH THEORY OF 
FLOW-FIELD MEASUREMENTS NEAR A LIFTING 
ROTOR IN THE LANGLEY FULL-SCALE TUNNEL. 
Harry H. Heyson. April 1956. 162p. diagrs., 
photos., tab. (NACA TN 3691) 



(1.6.2) 
EXPERIMENTAL STUDIES 

GUST -TUNNEL INVESTIGATION OF THE EFFECT 
OF A SHARP -EDGE GUST ON THE FLAPWISE 
BLADE BENDING MOMENTS OF A MODEL HELI- 
COPTER ROTOR. Domenic J. Maglieri and Thomas 
D. Reisert. August 1955. 24p. diagrs., photos. 
(NACA TN 3470) 



(1.6.2.1) 
POWER DRIVEN 

DETERMINATION OF INFLOW DISTRIBUTIONS 
FROM EXPERIMENTAL AERODYNAMIC LOADING 
AND BLADE-MOTION DATA ON A MODEL HELI- 
COPTER ROTOR IN HOVERING AND FORWARD 
FLIGHT. Gaetano Falabella, Jr., and John R. 
Meyer, Jr., Massachusetts Institute of Technology. 
November 1955. 184p. diagrs., photos., tab. 
(NACA TN 3492) 

ANALYSIS AND COMPARISON WITH THEORY OF 
FLOW -FIELD MEASUREMENTS NEAR A LIFTING 
ROTOR IN THE LANGLEY FULL-SCALE TUNNEL. 
Harry H. Heyson. April 1956. 162p. diagrs., 
photos., tab. (NACA TN 3691) 



69 



(1) AERODYNAMICS 



(1.7) 
Aircraft 



(1.7.1) 
AIRPLANES 



A UNIFIED TWO-DIMENSIONAL APPROACH TO 
THE CALCULATION OF THREE-DIMENSIONAL 
HYPERSONIC FLOWS, WITH APPLICATION TO 
BODIES OF REVOLUTION. A. J. Eggers, Jr. and 
Raymond C. Savin. 1955. ii, 27p. diagrs., tab. 
(NACA Rept. 1249. Supersedes TN 2811) 



(1.7. 1. 1) 

COMPO^WTQ TM rOURTNATTON 



a** fiC'rS Or A SWEPTBACK HYDROFOIL ON THE 
FORCE AND LONGITUDINAL STABILITY CHARAC- 
TERISTICS OF A TYPICAL HIGH-SPEED AIR- 
PLANE. Raymond B. Wood. December 2, 1948. 
19p. diagrs., photo., tabs. (NACA RM L8I30a) 



LARGE-SCALE FLIGHT MEASUREMENTS OF 
ZERO- LIFT DRAG AT MACH NUMBERS FROM 
0.86 TO 1.5 OF A WING-BODY COMBINATION 
HAVING A 60° TRIANGULAR WING WITH NACA 
65A003 SECTIONS. Robert L. Nelson. June 1, 
1950. lOp. diagrs., photos., tab. 
(NACA RM L50D26) 



LARGE-SCALE FLIGHT MEASUREMENTS OF 
ZERO-LIFT DRAG AT MACH NUMBERS FROM 0.8 
TO 1.6 OF A WING- BODY COMBINATION HAVING 
AN UNSWEPT 4.5-PERCENT-THICK WING WITH 
MODIFIED HEXAGONAL SECTIONS. Eugene D. 
Schult. March 23, 1951. 14p. diagrs., photos., tab. 
(NACA RM L51A15) 



INVESTIGATION OF THE EFFECT OF A NACELLE 
AT VARIOUS CHORDWISE AND VERTICAL POSI- 
TIONS ON THE AERODYNAMIC CHARACTERISTICS 
AT HIGH SUBSONIC SPEEDS OF A 45° SWEPTBACK 
WING WITH AND WITHOUT A FUSELAGE. 
H. Norman Silvers, Thomas J. King, Jr., and 
Thomas B. Pasteur, Jr. September 1951. 71p. 
diagrs., photos., 3 tabs. {NACA RM L51H16) 



LONGITUDINAL STABILITY, TRIM, AND DRAG 
CHARACTERISTICS OF A ROCKET-PROPELLED 
MODEL OF AN AIRPLANE CONFIGURATION HAV- 
ING A 45° SWEPTBACK WING AND AN UNSWEPT 
HORIZONTAL TAIL. James H. Parks and Alan B. 
Kehlet. August 1952. 29p. diagrs., photos., tab. 
(NACA RM L52F05) 



INVESTIGATION OF THE EFFECT OF CHORDWISE 
POSITIONING AND SHAPE OF AN UNDERWING NA- 
CELLE ON THE HIGH-SPEED AERODYNAMIC 
CHARACTERISTICS OF A 45° SWEPTBACK 
TAPERED-IN-THICKNESS-RATIO WING OF AS- 
PECT RATIO 6. H. Norman Silvers and Thomas J. 
King, Jr. January 1953. 50p. diagrs. 
(NACA RM L52K25) 



LARGE-SCALE FLIGHT MEASUREMENTS OF 
ZERO-LIFT DRAG AND LOW-LIFT LONGITUDINAL 
CHARACTERISTICS OF A DIAMOND-WING— BODY 
COMBINATION AT MACH NUMBERS FROM 0.725 
TO 1.54. Harvey A. Wallskog and John D. Morrow. 
April 1953. 18p. diagrs., photo., tab. 
(NACA RM L53C17) 



WIND-TUNNEL INVESTIGATION TO DETERMINE 
THE HORIZONTAL- AND VERTICAL-TAIL CON- 
TRIBUTIONS TO THE STATIC LATERAL STABIL- 
ITY CHARACTERISTICS OF A COMPLETE -MODEL 
SWEPT-WING CONFIGURATION AT HIGH SUBSON- 
IC SPEEDS. James W. Wiggins, Richard E. Kuhn, 
and Paul G. Fournier. Julv 1953. 34p. diagrs., 
photo. (NACA RM L53E19) 



LONGITUDINAL FLIGHT CHARACTERISTICS OF 
THE BELL X-5 RESEARCH AIRPLANE AT 59° 
SWEEPBACK WITH MODIFIED WING ROOTS. 
James A. Martin. August 1953. 25p. diagrs., 
photos., tab. (NACA RM L53E28) 



THEORY OF WING-BODY DRAG AT SUPERSONIC 
SPEEDS. Robert T. Jones. September 1953. lip. 
diagrs. (NACA RM A53H18a) 



ARRANGEMENT OF FUSIFORM BODIES TO RE- 
DUCE THE WAVE DRAG AT SUPERSONIC SPEEDS. 
Morris D. Friedman and Doris Cohen. 1955. ii, 
8p. diagrs. (NACA Rept. 1236. Supersedes 
RM A51I20; TN 3345) 



THE WAVE DRAG OF ARBITRARY CONFIGURA- 
TIONS IN LINEARIZED FLOW AS DETERMINED 
BY AREAS AND FORCES IN OBLIQUE PLANES. 
Harvard Lomax. Marrh 1955. 16p. 
(NACARMA55A18) 



A COMPARISON OF TWO METHODS FOR COMPUT- 
ING THE WAVE DRAG OF WING-BODY COMBINA- 
TIONS. Alberta Alksne. April 1955. 32p. diagrs. 
(NACA RM A55A06a) 



A SPECIAL METHOD FOR FINDING BODY DISTOR- 
TIONS THAT REDUCE THE WAVE DRAG OF WING 
AND BODY COMBINATIONS AT SUPERSONIC 
SPEEDS. Harvard Lomax and Max. A. Heaslet, 
May 1955. 113p. diagrs., tab. (NACA RM A55B16) 



70 



(1) AERODYNAMICS 



GENERAL THEORY OF WAVE-DRAG REDUCTION 
FOR COMBINATIONS EMPLOYING QUASI- 
CYLINDRICAL BODIES WITH AN APPLICATION TO 
SWEPT -WING AND BODY COMBINATIONS. Jack 
N. Nielsen. June 1955. 74p. diagrs. 
(NACA RM A55B07) 



WING-BODY COMBINATIONS WITH CERTAIN GEO- 
METRIC RESTRAINTS HAVING LOW ZERO-LIFT 
WAVE DRAG AT LOW SUPERSONIC MACH NUM- 
BERS. Harvard Lomax. February 1956. 32p. 
diagrs. (NACA TN 3667) 



SOME EFFECTS OF FUSELAGE FLEXIBILITY ON 
LONGITUDINAL STABILITY AND CONTROL. 
Bernard B. Klawans and Harold I. Johnson. April 
1956. 42p. diagrs., tab. (NACA TN 3543) 



PERFORMANCE AND OPERATIONAL STUDIES OF 
A FULL-SCALE JET-ENGINE THRUST REVERSER. 
Robert C. Kohl. April 1956. 38p. diagrs., photo. 
(NACA TN 3665) 



(1.7. 1. 1. 1) 
Wing -Fuselage 

THE HIGH-SPEED AERODYNAMIC EFFECTS OF 
MODIFICATIONS TO THE WING AND WING- 
FUSELAGE INTERSECTION OF AN AIRPLANE 
MODEL WITH THE WING SWEPT BACK 35°. Lee 
E. Boddy and Charles P. Morrill, Jr. February 18, 
1948. 34p. diagrs., photos. (NACA RM A7J02) 



LONGITUDINAL STABILITY CHARACTERISTICS OF 
A 42° SWEPTBACK WING AND TAIL COMBINATION 
AT A REYNOLDS NUMBER OF 6.8 x 10 6 . Stanley H. 
Spooner and Albert P. Martina. July 22, 1948. 
44p. diagrs., photos., 2 tabs. (NACA RM L8E12) 



LONGITUDINAL-STABILITY INVESTIGATION OF 
HIGH-LIFT AND STALL-CONTROL DEVICES ON A 
52° SWEPTBACK WING WITH AND WITHOUT FUSE- 
LAGE AND HORIZONTAL TAIL AT A REYNOLDS 
NUMBER OF 6.8 x 10 6 . Gerald V. Foster and 
James E. Fitzpatrick, December 20, 1948. 41p. 
diagrs., photos., tabs. (NACA RM L8I08) 



EFFECTS OF HIGH-LIFT AND STALL-CONTROL 
DEVICES, FUSELAGE, AND HORIZONTAL TAIL ON 
A WING SWEPT BACK 42° AT THE LEADING EDGE 
AND HAVING SYMMETRICAL CIRCULAR-ARC AIR- 
FOIL SECTIONS AT A REYNOLDS NUMBER OF 
6.9 x 10 6 . Robert L. Woods and Stanley H. 



Spooner. April 20, 1949. 
tabs. (NACA RM L9B11) 



42p. diagrs., photos., 



A STUDY OF SEVERAL FACTORS AFFECTING THE 
STABILITY CONTRIBUTED BY A HORIZONTAL 
TAIL AT VARIOUS VERTICAL POSITIONS ON A 
SWEPTBACK-WING AIRPLANE MODEL. Gerald V. 
Foster and Roland F. Griner. October 28, 1949. 
28p. diagrs., tab. (NACA RM L9H19) 



AERODYNAMIC CHARACTERISTICS AND FLYING 
QUALITIES OF A TAILLESS TRIANGULAR-WING 
AIRPLANE CONFIGURATION AS OBTAINED FROM 
FLIGHTS OF ROCKET-PROPELLED MODELS AT 
TRANSONIC AND LOW SUPERSONIC SPEEDS. 
Grady L. Mitcham, Joseph E. Stevens, and Harry P. 
Norris. February 9, 1950. 67p. diagrs., photos., 
tabs. (NACA RM L9L07) 



EFFECT OF WING-TANK LOCATION ON THE DRAG 
AND TRIM OF A SWEPT -WING MODEL AS MEAS- 
URED IN FLIGHT AT TRANSONIC SPEEDS. 
Clement J. Welsh and John D. Morrow. April 4, 
1950. 18p. diagrs., photos. (NACA RM L50A19) 



LARGE-SCALE FLIGHT MEASUREMENTS OF 
ZERO- LIFT DRAG AT MACH NUMBERS FROM 
0.86 TO 1.5 OF A WING -BODY COMBINATION 
HAVING A 60° TRIANGULAR WING WITH NACA 
65A003 SECTIONS. Robert L. Nelson. June 1, 
1950. lOp. diagrs., photos., tab. 
(NACARM L50D26) 



LIFT AND PITCHING-MOMENT INTERFERENCE 
BETWEEN A POINTED CYLINDRICAL BODY AND 
TRIANGULAR WINGS OF VARIOUS ASPECT RATIOS 
AT MACH NUMBERS OF 1.50 AND 2.02. Jack N. 
Nielsen, Elliott D. Katzen, and Kenneth K. Tang. 
September 12, 1950. 53p. diagrs., photos., tabs. 
(NACA RM A50F06) 



A TRANSONIC-WING INVESTIGATION IN THE 
LANGLEY 8-FOOT HIGH-SPEED TUNNEL AT HIGH 
SUBSONIC MACH NUMBERS AND AT A MACH 
NUMBER OF 1.2. WING-FUSELAGE CONFIGURA- 
TION WITH A WING OF 45° SWEEPBACK, ASPECT 
RATIO 4, TAJPER RATIO 0.6, AND NACA 65A006 
AIRFOIL SECTION. Robert S. Osborne. 
October 10, 1950. 49>. diagrs., photos. 
(NACA RM L50H08) 



TRANSONIC FLIGHT TESTS TO COMPARE THE 
ZERO-LIFT DRAG OF UNDERSLUNG AND SYM- 
METRICAL NACELLES VARIED CHORDWISE AT 
40 PERCENT SEMISPAN OF A 45° SWEPTBACK, 
TAPERED WING. William B. Pepper, Jr., and 
Sherwood Hoffman. October 25, 1950. 36p. 
diagrs,, photos., tabs. (NACA RM L50G17a) 



A TRANSONIC WING INVESTIGATION IN THE 
LANGLEY 8-FOOT HIGH-SPEED TUNNEL AT HIGH 
SUBSONIC MACH NUMBERS AND AT A MACH 
NUMBER OF 1.2. WING-FUSELAGE CONFIGURA- 
TION HAVING A WING OF 35° SWEEPBACK, AS- 
PECT RATIO 4, TAPER RATIO 0.6, AND NACA 
65A006 AIRFOIL SECTION. Beverly Z. Henry, Jr. 
November 15, 1950. 40p. diagrs., photo., tab. 
(NACA RM L50J09) 



A TRANSONIC -WING INVESTIGATION IN THE 
LANGLEY 8-FOOT HIGH-SPEED TUNNEL AT HIGH 
SUBSONIC MACH NUMBERS AND AT A MACH NUM- 
BER OF 1.2. WING-FUSELAGE CONFIGURATION 
HAVING A WING OF 60° SWEEPBACK, ASPECT 
RATIO 4, TAPER RATIO 0.6, AND NACA 65A006 
AIRFOIL SECTION. Raymond B. Wood and Frank F. 
Fleming. January 24, 1951. 43p. diagrs., photo. 
(NACA RM L50J25) 



71 



(1) AERODYNAMICS 



AERODYNAMIC CHARACTERISTICS INCLUDING 
PRESSURE DISTRIBUTIONS OF A FUSELAGE AND 
THREE COMBINATIONS OF THE FUSELAGE WITH 
SWEPT-BACK WINGS AT HIGH SUBSONIC SPEEDS. 
Fred B, Sutton and Andrew Martin. February 6, 
1951. 117p. diagrs., photos., tabs. 
(NACA RM A50J26a) 



LOW-SPEED LONGITUDINAL AND WAKE AIR- 
FLOW CHARACTERISTICS AT A REYNOLDS NUM- 
BER OF 6.0 x 10 6 OF A 52° SWEPTBACK WING 
EQUIPPED WITH VARIOUS SPANS OF LEADING- 
EDGE AND TRAILING-EDGE FLAPS, A FUSELAGE, 
AND A HORIZONTAL TAIL AT VARIOUS VERTICAL 
POSITIONS. Roland F. Griner and Gerald V. Foster. 
February 28, 1951. 66p. diagrs., photo., 3 tabs. 
{NACA RM L50K29) 



A TRANSONIC -WING INVESTIGATION IN THE 
LANGLEY 8-FOOT HIGH-SPEED TUNNEL AT 
HIGH SUBSONIC MACH NUMBERS AND AT A 
MACH NUMBER OF 1.2. WING-FUSELAGE CON- 
FIGURATION HAVING A WING OF 0° SWEEPBACK, 
ASPECT RATIO 4.0, TAPER RATIO 0.6, AND NACA 
65A006 AIRFOIL SECTION. Maurice S. Cahn and 
Carroll R. Bryan. March 6, 1951. 37p. diagrs., 
photos. (NACA RM L51A02) 



LARGE-SCALE FLIGHT MEASUREMENTS OF 
ZERO- LIFT DRAG AT MACH NUMBERS FROM 0.8 
TO 1.6 OF A WING-BODY COMBINATION HAVING 
AN UNSWEPT 4. 5 -PERCENT -THICK WING WITH 
MODIFIED HEXAGONAL SECTIONS. Eugene D. 
Schult. March 23, 1951. 14p. diagrs., photos., tab. 
(NACA RM L51A15) 



DRAG INTERFERENCE BETWEEN A POINTED 
CYLINDRICAL BODY AND TRIANGULAR WINGS OF 
VARIOUS ASPECT RATIOS AT MACH NUMBERS OF 
1.50 AND 2.02. Elliott D. Katzen and George E. 
Kaattari. May 23, 1951. 45p. diagrs., photos., tabs. 
(NACA RM A51C27) 



COMPARISON OF ZERO-LIFT DRAGS DETER- 
MINED BY FLIGHT TESTS AT TRANSONIC SPEEDS 
OF SYMMETRICALLY MOUNTED NACELLES IN 
VARIOUS SPANWISE POSITIONS ON A 45° SWEPT- 
BACK WING AND BODY COMBINATION. William B. 
Pepper, Jr., and Sherwood Hoffman. May 23, 1951. 
29p. diagrs., photos., tabs. (NACA RM L51D06) 



COMPARISON OF ZERO -LIFT DRAG DETERMINED 
BY FLIGHT TESTS AT TRANSONIC SPEEDS OF 
PYLON, UNDERSLUNG, AND SYMMETRICALLY 
MOUNTED NACELLES AT 40 PERCENT SEMISPAN 
OF A 45° SWEPTBACK WING AND BODY COMBINA- 
TION. Sherwood Hoffman. June 1951. 18p. diagrs., 
photos,, tabs. (NACA RM L51D26) 



AERODYNAMIC CHARACTERISTICS OF FOUR 
WINGS OF SWEEPBACK ANGLES 0°, 35°, 45°, AND 
60°, NACA 65A006 AIRFOIL SECTION, ASPECT 
RATIO 4, AND TAPER RATIO 0.6 IN COMBINATION 
WITH A FUSELAGE AT HIGH SUBSONIC MACH 
NUMBERS AND AT A MACH NUMBER OF 1.2. 
Arvo A. Luoma. June 6, 1951. 59p. diagrs., photo., 
tab. (NACA RM L51D13) 



LOW -SPEED LONGITUDINAL AND WAKE AIR- 
FLOW CHARACTERISTICS AT A REYNOLDS NUM- 
BER OF 5.5 x 10 6 OF A CIRCULAR-ARC 52° 
SWEPTBACK WING WITH A FUSELAGE AND A 
HORIZONTAL TAIL AT VARIOUS VERTICAL POSI- 
TIONS. Gerald V. Foster and Roland F. Griner. 
June 19, 1951. 44p. diagrs., tabs. 
(NACA RM L51C30) 



INVESTIGATION OF THE EFFECTS OF TWIST AND 
CAMBER ON THE AERODYNAMIC CHARACTER- 
ISTICS OF A 50° 38' SWEPTBACK WING OF AS- 
PECT RATIO 2.98. TRANSONIC -BUMP METHOD. 
Kenneth P. Spreemann and William J. Alford, Jr. 
August 1951. 33p. diagrs., photos., tab, 
(NACA RM L51C16) 



TRANSONIC -WING INVESTIGATION IN THE 
LANGLEY 8-FOOT HIGH-SPEED TUNNEL AT HIGH 
SUBSONIC MACH NUMBERS AND AT A MACH NUM- 
BER OF 1.2. ANALYSIS OF PRESSURE DISTRIBU- 
TION OF WING-FUSELAGE CONFIGURATION HAV- 
ING A WING OF 45° SWEEPBACK, ASPECT RATIO 
4, TAPER RATIO 0.6, AND NACA 65A006 AIRFOIL 
SECTION. Donald L, Loving and Bruce B. 
Estabrooks. September 1951. 132p. diagrs., photos. 
(NACA RM L51F07) 



COMPARISON OF ZERO-LIFT DRAGS DETER- 
MINED BY FLIGHT TESTS AT TRANSONIC SPEEDS 
OF SYMMETRICALLY MOUNTED NACELLES IN 
VARIOUS CHORDWISE POSITIONS AT THE WING 
TIP OF A 45° SWEPTBACK WING AND BODY 
COMBINATION. William B. Pepper, Jr., and 
Sherwood Hoffman. September 1951. 16p. diagrs., 
photos. (NACA RM L51F13) 



THE EFFECT ON ZERO-LIFT DRAG OF AN IN- 
DENTED FUSELAGE OR A THICKENED WING-ROOT 
MODIFICATION TO A 45° SWEPTBACK WING-BODY 
CONFIGURATION AS DETERMINED BY FLIGHT 
TESTS AT TRANSONIC SPEEDS. William B. 
Pepper. September 1951. 20p. diagrs., photos., 
2 tabs. (NACA RM L51F15) 

TRANSONIC FLIGHT TESTS TO DETERMINE 
ZERO-LIFT DRAG AND PRESSURE RECOVERY OF 
NACELLES LOCATED AT THE WING TIPS ON A 
45° SWEPTBACK WING AND BODY COMBINATION. 
Sherwood Hoffman and William B. Pepper, Jr. 
January 1952. 21p. diagrs., photos., tabs. 
(NACA RM L51K02) 

FLIGHT CALIBRATION OF ANGLE-OF-ATTACK 
AND SIDESLIP DETECTORS ON THE FUSELAGE 
OF A 35° SWEPT -WING FIGHTER AIRPLANE. 
Norman M. McFadden, George A. Rathert, Jr., and 
RichardS. Bray. February 1952. 26p. diagrs,, 
photos. (NACA RM A52A04) 

TRANSONIC FLIGHT TESTS TO COMPARE THE 
ZERO-LIFT DRAGS OF 45° SWEPTBACK WINGS OF 
ASPECT RATIO 3.55 AND 6.0 WITH AND WITHOUT 
NACELLES AT THE WING TIPS. Sherwood Hoffman 
and Richard C. Mapp. Jr. March 1952, 17p. 
diagrs., photos. (NACA RM L51L27) 

WIND-TUNNEL INVESTIGATION OF THE AERODY- 
NAMIC CHARACTERISTICS IN PITCH OF WING- 
FUSELAGE COMBINATIONS AT HIGH SUBSONIC 
SPEEDS. ASPECT-RATIO SERIES. Richard E, 
Kuhn and James W. Wiggins. April 1952. 42p. 
diagrs., photos., tab. (NACA RM L52A29) 



72 



(1) AERODYNAMICS 



TRANSONIC DRAG CHARACTERISTICS AND PRES- 
SURE DISTRIBUTION ON THE BODY OF A WING- 
BODY COMBINATION CONSISTING OF A BODY OF 
REVOLUTION OF FINENESS RATIO 12 AND A WING 
HAVING SWEEPBACK OF 45°, ASPECT RATIO 4, 
TAPER RATIO 0.6, AND NACA 65A006 AIRFOIL 
SECTIONS. Max C. Kurbjun and Jim Rogers 
Thompson. April 1952. 28p. diagrs., photo., tabs. 
(NACA RML52B12) 



USE OF AN AERODYNAMICALLY PULSED ALL- 
MOVABLE HORIZONTAL TAIL TO OBTAIN LONGI- 
TUDINAL CHARACTERISTICS OF ROCKET- 
POWERED MODELS IN FREE FLIGHT AND SOME 
INITIAL RESULTS FROM AN ARROW -WING -BODY - 
TAIL CONFIGURATION. Warren Gillespie, Jr., and 
Albert E. Dietz. May 1952. 31p. diagrs., photos. 
(NACA RM L52C10) 



AN INVESTIGATION THROUGHOUT THE SUBSONIC 
SPEED RANGE OF A FULL-SPAN AND A SEMI- 
SPAN MODEL OF A PLANE WING AND OF A 
CAMBERED AND TWISTED WING, ALL HAVING 
45° OF SWEEPBACK. Harry H. Shibata, Angelo 
Bandettini, and Joseph Cleary. June 1952. 65p. 
diagrs., photos. (NACA RM A52D01) 



A STUDY OF THE FLOW OVER A 45° SWEPTBACK 
WING- FUSELAGE COMBINATION AT TRANSONIC 
MACH NUMBERS. Richard T. Whitcomb and 
Thomas C. Kelly. June 1952. 60p. diagrs., 
photos. {NACA RM L52D01) 



TRANSONIC FLIGHT TESTS TO COMPARE THE 
ZERO-LIFT DRAGS OF UNDERSLUNG NACELLES 
VARIED SPANWISE ON A 45° SWEPTBACK WING 
AND BODY COMBINATION. Sherwood Hoffman. 
July 1952. 16p. diagrs., photos. 
(NACA RM L52D04a) 



WIND-TUNNEL INVESTIGATION OF THE AERO- 
DYNAMIC CHARACTERISTICS IN PITCH OF WING- 
FUSELAGE COMBINATIONS AT HIGH-SUBSONIC 
SPEEDS. SWEEP SERIES. James W. Wiggins and 
Richard E. Kuhn. July 1952. 41p. diagrs., photos. 
(NACA RM L52D18) 



EFFECT OF FUSELAGE INTERFERENCE ON THE 
DAMPING IN ROLL OF DELTA WINGS OF ASPECT 
RATIO 4 IN THE MACH NUMBER RANGE BETWEEN 
0.6 AND 1.6 AS DETERMINED WITH ROCKET- 
PROPELLED VEHICLES. William M. Bland, Jr. 
July 1952. 13p. diagrs., photos. (NACA RM L52E13) 



TRANSONIC FLIGHT TESTS TO DETERMINE THE 
EFFECT OF THICKNESS RATIO AND PLAN-FORM 
MODIFICATION ON THE ZERO-LIFT DRAG OF A 
45° SWEPTBACK WING. William B. Pepper, Jr., 
and Sherwood Hoffman. August 1952. 24p. diagrs., 
photos., tabs. (NACA RM L52F02a) 



FREE-FLIGHT TESTS AT MACH NUMBERS FROM 
8 TO 1.4 TO DETERMINE THE EFFECT ON 
ZERO-LIFT DRAG OF INCREASING THE LEADING- 
EDGE BLUNTNESS OF A 45° SWEPTBACK WING 
HAVING AN NACA 65A009 AIRFOIL. William B. 
Pepper, Jr. August 1952. 15p. diagrs., photos., 
tabs. (NACA RM L52F30) 



PRELIMINARY RESULTS OF HORIZONTAL-TAIL 
LOAD MEASUREMENTS OF THE BELL X T 5 RE- 
SEARCH AIRPLANE, JohnT. Rogers and Angel H. 
Dunn. August 15, 1952. 22p. diagrs., photos., 
tabs. (NACA RM L52G14) 



THE LONGITUDINAL CHARACTERISTICS AT MACH 
NUMBERS UP TO 0.92 OF A CAMBERED AND > 
TWISTED WING HAVING 40° OF SWEEPBACK AND 
AN ASPECT RATIO OF 10. George G. Edwards, 
Bruce E. Tinling, and Arthur C. Ackerman. 
September 1952. 71p, diagrs., photos., tab. 
(NACA RM A52F18) 



A STUDY OF THE ZERO-LIFT DRAG-RISE CHAR- 
ACTERISTICS OF WING-BODY COMBINATIONS 
NEAR THE SPEED OF SOUND. Richard T. 
Whitcomb. September 1952. 41p. diagrs., photos., 
3 tabs. (NACA RM L52H08) 



LONGITUDINAL-CONTROL EFFECTIVENESS AND 
DOWNWASH CHARACTERISTICS AT TRANSONIC 
SPEEDS OF A 1/30-SCALE SEMISPAN MODEL OF 
THE BELL X-5 AIRPLANE AS DETERMINED BY 
THE NACA WING -FLOW METHOD. Norman S. 
Silsby and Garland J. Morris. January 1953. 48p. 
diagrs., photos., 2 tabs. (NACA RM L52K12) 



WIND-TUNNEL INVESTIGATION OF THE STATIC 
LATERAL STABILITY CHARACTERISTICS OF 
WING-FUSELAGE COMBINATIONS AT HIGH SUB- 
SONIC SPEEDS. ASPECT-RATIO SERIES. Paul G. 
Fournier and Andrew L. Byrnes, Jr. February 1953. 
26p. diagrs., photos. (NACA RM L52L18) 



LOW-SPEED LONGITUDINAL CHARACTERISTICS 
OF AN UNSWEPT HEXAGONAL WING WITH AND 
WITHOUT A FUSELAGE AND A HORIZONTAL TAIL 
LOCATED AT VARIOUS POSITIONS AT REYNOLDS 
NUMBERS FROM 2.8 x 10 6 TO 7.6 x 10 6 . Gerald V. 
Foster. Ernst F. Mollenberg, and Robert L. Woods. 
February 26, 1953. 63p. diagrs., photos., 3 tabs. 
(NACA RM L52Lllb) 



PRESSURE DISTRIBUTION AT MACH NUMBERS UP 
TO 0.90 ON A CAMBERED AND TWISTED WING 
HAVING 40° OF SWEEPBACK AND AN ASPECT 
RATIO OF 10, INCLUDING THE EFFECTS OF 
FENCES. Frederick W. Boltz and Harry H. 
Shibata. March 1953. 133p. diagrs., photos., tabs. 
(NACA RM A52K20) 



COMPARISON OF MEASURED AND PREDICTED 
INDICATED ANGLES OF ATTACK NEAR THE 
FUSELAGES OF A TRIANGULAR-WING WIND- 
TUNNEL MODEL AND A SWEPT -WING FIGHTER 
AIRPLANE IN FLIGHT. Norman M. McFadden, 
John L. McCloud, III, and Harry A. James. 
March 1953. 13p. diagrs. (NACA RM A53A15) 



THE EFFECTS OF COMPRESSIBILITY ON THE 
UPWASH AT THE PROPELLER PLANES OF A 
FOUR-ENGINE TRACTOR AIRPLANE CONFIGURA- 
TION HAVING A WING WITH 40° OF SWEEPBACK 
AND AN ASPECT RATIO.OF 10. Armando E. 
Lopez and Jerald K. Dickson. April 1953. 38p. 
diagrs., photos., tab. (NACA RM A53A30a) 



73 



(1) AERODYNAMICS 



LARGE-SCALE FLIGHT MEASUREMENTS OF 
ZERO-LIFT DRAG AND LOW-LIFT LONGITUDINAL 
CHARACTERISTICS OF A DIAMOND-WING —BODY 
COMBINATION AT MACH NUMBERS FROM 0.725 
TO 1.54. Harvey A. Waiiskog and John D. Morrow. 
April 1953. 18p. diagrs., photo., tab. 
(NACA RM L53C17) 



EXPERIMENTAL INVESTIGATION OF THE EF- 
FECTS OF PLAN-FORM TAPER ON THE AERO- 
DYNAMIC CHARACTERISTICS OF SYMMETRICAL 
UNSWEPT WINGS OF VARYING ASPECT RATIO. 
Edwin C. Allen. May 1953. 53p. diagrs., photos., 
tab. (NACA RM A53C19) 



LOW-SPEED INVESTIGATION OF THE AERODY- 
NAMIC, CONTROL, AND HINGE-MOMENT CHAR- 
ACTERISTICS OF TWO TYPES OF CONTROLS ON 
A DELTA-WING-FUSELAGE MODEL WITH AND 
WITHOUT NACELLES. William I. Scallion. May 
1953. 47p. diagrs., photos., tabs. 
(NACA RM L53C18) 



FREE-FALL MEASUREMENTS OF THE EFFECTS 
OF WING-BODY INTERFERENCE ON THE TRAN- 
SONIC DRAG CHARACTERISTICS OF SWEPT-WING- 
SLENDER-BODY CONFIGURATIONS. Max C. 
Kurbjun and Jim Rogers Thompson. May 1953. 34p, 
diagrs., photos., tabs. (NACA RM L53C31) 



LONGITUDINAL STABILITY AND WAKE-FLOW 
CHARACTERISTICS OF A TWISTED AND 
CAMBERED WING-FUSELAGE COMBINATION OF 
45° SWEEPBACK AND ASPECT RATIO 8 WITH A 
HORIZONTAL TAIL AND STALL-CONTROL DE- 
VICES AT A REYNOLDS NUMBER OF 4.0 x 10 6 . 
Gerald V. Foster. June 1953. 51p. diagrs., 
photos., tab. (NACA RM L53D08) 



WIND-TUNNEL INVESTIGATION OF THE AERODY- 
NAMIC CHARACTERISTICS IN PITCH OF WING- 
FUSELAGE COMBINATIONS AT HIGH SUBSONIC 
SPEEDS. TAPER- RATIO SERIES. Thomas J. 
King. Jr. and Thomas B. Pasteur, Jr. June 1953. 
37p. diagrs., photos., tab. (NACA RM L53E20) 



WIND-TUNNEL INVESTIGATION OF THE EFFECTS 
OF GEOMETRIC DIHEDRAL ON THE AERODYNAM- 
IC CHARACTERISTICS IN PITCH AND SIDESLIP OF 
AN UNSWEPT- AND A 45° SWEPTBACK-WING- 
FUSELAGE COMBINATION AT HIGH SUBSONIC 
SPEEDS. Richard E. Kuhn and John W. Draper. 
July 1953. 41p. diagrs., photos. 
(NACA RM L53F09) 



THE EFFECTS OF LEADING-EDGE EXTENSIONS, 
A TRAILING-EDGE EXTENSION, AND A FENCE 
ON THE STATIC LONGITUDINAL STABILITY OF A 
WING-FUSELAGE-TAIL COMBINATION HAVING 
A WING WITH 35° OF SWEEPBACK AND AN AS- 
PECT RATIO OF 4.5. Ralph Selan and Angelo 
Bandettini. August 1953. 81p. diagrs., photos., 
tabs. (NACA'RM A53E12) 



THE LATERAL CONTROL CHARACTERISTICS OF 
CONSTANT-PERCENT-CHORD TRAILING-EDGE 
ELEVONS ON A POINTED WING OF ASPECT RATIO 
2 AT MACH NUMBERS UP TO 0.95. Verlin D. Reed 
and Donald W. Smith. August 1953. 105u. diagrs., 
photo., tabs. (NACARMA53F03) 



WIND-TUNNEL INVESTIGATION OF THE EFFECTS 
OF STEADY ROLLING ON THE AERODYNAMIC 
LOADING CHARACTERISTICS OF A 45° SWEPT- 
BACK WING AT HIGH SUBSONIC SPEEDS. James 
W. Wiggins and Richard E. Kuhn. November 1953. 
22p. diagrs., photos. (NACA RM L53J01a) 



WIND-TUNNEL INVESTIGATION AT LOW SPEED 
OF THE EFFECT OF VARYING THE RATIO OF 
BODY DIAMETER TO WING SPAN FROM 0.1 TO 0.8 
ON THE AERODYNAMIC CHARACTERISTICS IN 
PITCH OF A 45° SWEPTBACK-WING— BODY 
COMBINATION. Harold S. Johnson. November 
1953. 32p. diagrs., photo., tab. 
(NACA RM L53J09a) 



WIND-TUNNEL INVESTIGATION AT LOW SPEED 
OF THE EFFECTS OF CHORDWISE WING FENCES 
AND HORIZONTAL-TAIL POSITION ON THE 
STATIC LONGITUDINAL STABILITY CHARACTER- 
ISTICS OF AN AIRPLANE MODEL WITH A 35° 
SWEPTBACK WING. M. J. Queijo, Byron M. 
Jaquet, and Walter D. Wolhart. 1954. 11, 29p. 
diaers.. photos., tab. (NACA Rept. 1203. Super- 
sedes RM L50K07; RM L51H17) 



THE EFFECTS OF HORIZONTAL-TAIL HEIGHT 
AND A PARTIAL-SPAN LEADING-EDGE EXTEN- 
SION ON THE STATIC LONGITUDINAL STABILITY 
OF A WING-FUSELAGE-TAIL COMBINATION 
HAVING A SWEPTBACK WING. Angelo Bandettini 
and Ralph Selan. March 1954. 54p. diagrs., 
photos., 2 tabs. (NACA RM A53J07) 



PRELIMINARY INVESTIGATION AT SUBSONIC AND 
TRANSONIC SPEEDS OF THE AERODYNAMIC 
CHARACTERISTICS OF A BIPLANE COMPOSED OF 
A SWEPTBACK AND A SWEPTFORWARD WING 
JOINED AT THE TIPS. Jones F. Cahill and 
Dexter H. Stead. March 1954. 19p. diagrs., 
photos. (NACA RM L53L24b) 



DISTRIBUTION OF LIFT AND PITCHING MOMENT 
BETWEEN WING AND FUSELAGE AND EFFECTS 
OF WING FLEXIBILITY AND DIVE BRAKE ON A 
1/ 30-SCALE SEMISPAN MODEL OF THE BELL X-5 
AIRPLANE AT TRANSONIC SPEEDS AS DETER- 
MINED BY THE NACA WING-FLOW METHOD. 
Garland J. Morris and Norman S. Silsby. March 
1054. 4Cp. diagrs., photos., tab. 
(NACARM L54A11) 



ON SLENDER-BODY THEORY AT TRANSONIC 
SPEEDS. Keith C. Harder and E. B. Klunker. 
March 1954. 12p. (NACA RM L54A29a) 



EFFECTS OF OPERATING PROPELLERS ON THE 
WING-SURFACE PRESSURES OF A FOUR-ENGINE 
TRACTOR AIRPLANE CONFIGURATION HAVING A 
WING WITH 40° OF SWEEPBACK. Carl D. Kolbe 
and Frederick W. Boltz. April 1954. 133p. 
diagrs., photo., 19 tabs. (NACA RM A53L29) 



74 



(1) AERODYNAMICS 



SUBSONIC INVESTIGATION OF EFFECTS OF BODY 
INDENTATION ON ZERO-LIFT DRAG CHARACTER- 
ISTICS OF A 45° SWEPTBACK WING-BODY COMBI- 
NATION WITH NATURAL AND FIXED BOUNDARY- 
LAYER TRANSITION THROUGH A RANGE OF 
REYNOLDS NUMBER FROM 1 x 10 6 TO 8 x 10 6 . 
Gene J. Bingham and Albert L. Braslow. April 1954. 
[Op. diagrs., photos. (NACA RM L54Bl8a) 

EFFECTS OF HIGH-LIFT DEVICES AND 
HORIZONTAL -TAIL LOCATION ON THE LOW- 
SPEED CHARACTERISTICS OF A LARGE-SCALE 
45° SWEPT-WING AIRPLANE CONFIGURATION. 
Ralph L. Maki and Ursel R. Embry. August 1954. 
46p. diagrs., photo., tabs. (NACA RM A54E10) 

APPLICATION OF WING-BODY THEORY TO DRAG 
REDUCTION AT LOW SUPERSONIC SPEEDS. 
Barrett S. Baldwin, Jr. , and Robert R. Dickey. 
January 1955. 42p. (NACA RM A54J19) 

DOWNWASH SURVEY BEHIND TWO LOW-ASPECT- 
RATIO VARIABLE-INCIDENCE WINGS IN COMBI- 
NATION WITH THREE DIFFERENT SIZE FUSE- 
LAGES AT A MACH NUMBER OF 0,25. Edward J. 
Hopkins and Norman E. Sorensen. March 1955. 54p. 
diagrs., photos., tab. (NACA RM A55A07) 

GENERAL THEORY OF WAVE-DRAG REDUCTION 
FOR COMBINATIONS EMPLOYING QUASI- 
CYLINDRICAL BODIES WITH AN APPLICATION TO 
SWEPT-WING AND BODY COMBINATIONS. Jack 
N. Nielsen. June 1955. 74p. diagrs. 
(NACA RM A55B07) 

FLIGHT MEASUREMENTS OF HORIZONTAL-TAIL 
LOADS ON THE BELL X-5 RESEARCH AIRPLANE 
AT A SWEEP ANGLE OF 58.7°. Robert D. Reed. 
July 1955. 19p. diagrs., photo., tab. 
(NACA RM H55E20a) 

THE EFFECTIVENESS OF WING VORTEX GENERA- 
TORS IN IMPROVING THE MANEUVERING CHARAC- 
TERISTICS OF A SWEPT-WING AIRPLANE AT 
TRANSONIC SPEEDS. Norman M. McFadden, 
George A. Rathert, Jr. , and Richard S. Bray. 
September 1955. 43p. diagrs., photos., tab. 
(NACA TN 3523. Supersedes RM A51J18) 

SUMMARY OF RESULTS OBTAINED BY 
TRANSONIC -BUMP METHOD ON EFFECTS OF 
PLAN FORM AND THICKNESS ON LIFT AND DRAG 
CHARACTERISTICS OF WINGS AT TRANSONIC 
SPEEDS. Edward C. Polhamus. November 1955. 
33p. diagrs., tab. (NACA TN 3469. Supersedes 
RM L51H30) 

MINIMUM WAVE DRAG FOR ARBITRARY AR- 
RANGEMENTS OF WINGS AND BODIES. Robert T. 
Jones. February 1956. lip. diagrs. 
(NACA TN 3530) 



REDUCTION OF WAVE DRAG OF WING- BODY 
COMBINATIONS AT SUPERSONIC SPEEDS 
THROUGH BODY DISTORTIONS. William C. Pitts. 
April 1956. 9p. diagrs. (NACA RM A56B10) 



AN ANALYSIS OF ESTIMATED AND EXPERI- 
MENTAL TRANSONIC DOWNWASH CHARACTER- 
ISTICS AS AFFECTED BY PLAN FORM AND THICK- 
NESS FOR WING AND WING- FUSELAGE CONFIG- 
URATIONS. Joseph Weil, George S. Campbell and 
Margaret S. Diederich. April 1956. 92p. diagrs., 
photos., tabs. (NACA TN 3628. Supersedes 
RM L52I22) 



RESULTS OF A FLIGHT INVESTIGATION TO DE- 
TERMINE THE ZERO-LIFT DRAG CHARACTER- 
ISTICS OF A 60° DELTA WING WITH NACA 65-006 
AIRFOIL SECTION AND VARIOUS DOUBLE-WEDGE 
SECTIONS AT MACH NUMBERS FROM 0.7 TO 1.6. 
Clement J. Welsh. April 1956. 13p. diagrs., 
photo. (NACA TN 3650. Supersedes RM L50F01) 



INVESTIGATION AT HIGH SUBSONIC SPEEDS OF A 
BODY-CONTOURING METHOD FOR ALLEVIATING 
THE ADVERSE INTERFERENCE AT THE ROOT OF 
A SWEPTBACK WING. John B. McDevitt and 
William M. Haire. April 1956. 38p. diagrs., 
photos. (NACA TN 3672. Supersedes RM A54A22) 



THEORETICAL PRESSURE DISTRIBUTIONS FOR 
SOME SLENDER WING-BODY COMBINATIONS AT 
ZERO LIFT. Paul F. Byrd. April 1956. 39p. 
diagrs. (NACA TN 3674. Supersedes RM A54J07) 



STATIC LONGITUDINAL AND LATERAL STABILITY 
CHARACTERISTICS AT LOW SPEED OF UNSWEPT- 
MTDWING MODELS HAVING WINGS WITH AN 
ASPECT RATIO OF 2, 4, OR 6. Walter D. Wolhart 
and David F. Thomas, Jr. May 1956. 41p. 
diagrs., photos., tabs. (NACA TN 3649) 



COMPARISON BETWEEN EXPERIMENTAL AND 
PREDICTED DOWNWASH AT A MACH NUMBER OF 
0.25 BEHIND A WING -BODY COMBINATION HAVING 
A TRIANGULAR WING OF ASPECT RATIO 2.0. 
Norman E. Sorensen and Edward J. Hopkins. May 
1956. 29p. diagrs., photos. (NACA TN 3720) 



(1.7. 1. 1. 2) 

Wing-Nacelle 



EXPERIMENTAL INVESTIGATION OF VARIOUS 
WING-MOUNTED EXTERNAL STORES ON A WING- 
FUSELAGE COMBINATION HAVING A SWEPTBACK 
WING OF INVERSE TAPER RATIO. Kenneth P. 
Spreemann and H. Norman Silvers. September 15, 
1950. 29p. diagrs., photos., tab. (NACA RM L9J06) 



TRANSONIC FLIGHT TESTS TO COMPARE THE 
ZERO-LIFT DRAG OF UNDERSLUNG AND SYM- 
METRICAL NACELLES VARIED CHORDWISE AT 
40 PERCENT SEMISPAN OF A 45° SWEPTBACK, 
TAPERED WING. William B. Pepper, Jr., and 
Sherwood Hoffman. October 25, 1950. 36p. 
diagrs,, photos., tabs. (NACA RM L50G17a) 



INVESTIGATION OF THE EFFECTS OF GEO- 
METRIC CHANGES IN AN UNDERWING PYLON- 
SUSPENDED EXTERNAL-STORE INSTALLATION 
ON THE AERODYNAMIC CHARACTERISTICS OF A 
45° SWEPTBACK WING AT HIGH SUBSONIC 
SPEEDS. Kenneth P. Spreemann and William J. 
Alford, Jr. March 5, 1951. 91p. diagrs., photos., 
tabs. (NACA RM L50L12) 



COMPARISON OF ZERO-LIFT DRAGS DETER- 
MINED BY FLIGHT TESTS AT TRANSONIC-SPEEDS 
OF SYMMETRICALLY MOUNTED NACELLES IN 
VARIOUS SPANWISE POSITIONS ON A 45° SWEPT- 
BACK WING AND BODY COMBINATION. William B. 
Pepper, Jr., and Sherwood Hoffman. May 23, 1951. 
29p. diagrs., photos., tabs. (NACA RM L51D06) 



75 



(1) AERODYNAMICS 



COMPARISON OF ZERO-LIFT DRAG DETERMINED 
BY FLIGHT TESTS AT TRANSONIC SPEEDS OF 
PYLON, UNDERSLUNG, AND SYMMETRICALLY 
MOUNTED NACELLES AT 40 PERCENT SEMISPAN 
OF A 450 SWEPTBACK WING AND BODY COMBINA- 
TION. Sherwood Hoffman. June 1951. 16p. diagrs., 
photos., tabs. (NACA RM L51D26) 



COMPARISON OF ZERO-LIFT DRAGS DETER- 
MINED BY FLIGHT TESTS AT TRANSONIC SPEEDS 
OF SYMMETRICALLY MOUNTED NACELLES IN 
VARIOUS CHORDWISE POSITIONS AT THE WING 
TIP OF A 45° SWEPTBACK WING AND BODY 
COMBINATION. William B. Pepper, Jr., and 
Sherwood Hoffman. September 1951. 16p. diagrs., 
photos. (NACA RM L51F13) 



TRANSONIC FLIGHT TESTS TO DETERMINE 
ZERO-LIFT DRAG AND PRESSURE RECOVERY OF 
NACELLES LOCATED AT THE WING TIPS ON A 
45° SWEPTBACK WING AND BODY COMBINATION. 
Sherwood Hoffman and William B. Pepper, Jr. 
January 1952. 21 p. diagrs., photos., tabs. 
(NACA RM L51K02) 



TRANSONIC FLIGHT TESTS TO COMPARE THE 
ZERO-LIFT DRAGS OF 45° SWEPTBACK WINGS OF 
ASPECT RATIO 3.55 AND 6.0 WITH AND WITHOUT 
NACELLES AT THE WING TIPS. Sherwood Hoffman 
and Richard C. Mapp. Jr. March 1952. 17p. 
diagrs., photos. (NACA RM L51L27) 



TRANSONIC FLIGHT TESTS TO COMPARE THE 
ZERO-LIFT DRAGS OF UNDERSLUNG NACELLES 
VARIED SPANWISE ON A 45° SWEPTBACK WING 
AND BODY COMBINATION. Sherwood Hoffman. 
July 1952. 16p. diagrs., photos. 
(NACA RM L52D04a) 



THE EFFECTS OF COMPRESSIBILITY ON THE 
UPWASH AT THE PROPELLER PLANES OF A 
FOUR-ENGINE TRACTOR AIRPLANE CONFIGURA- 
TION HAVING A WING WITH 40° OF SWEEPBACK 
AND AN ASPECT RATIO. OF 10. Armando E. 
Lopez and Jerald K. Dickson. April 1953. 38p. 
diagrs., photos., tab. (NACA RM A53A30a) 



LOW-SPEED INVESTIGATION OF THE AERODY- 
NAMIC, CONTROL, AND HINGE-MOMENT CHAR- 
ACTERISTICS OF TWO TYPES OF CONTROLS ON 
A DELTA-WING-FUSELAGE MODEL WITH AND 
WITHOUT NACELLES. William I. Scalllon. May 
1953. 47p. diagrs., photos., tabs. 
(NACA RM L53C18) 



THE EFFECTS OF NACELLES AND OF EXTENDED 
SPLIT FLAPS ON THE LONGITUDINAL CHARAC- 
TERISTICS OF A WING-FUSELAGE-TAIL COMBI- 
NATION HAVING A WING WITH 40° OF SWEEP - 
BACK AND AN ASPECT RATIO OF 10. Bruce E. 
Tinling and Armando E. Lopez. June 1953. 47p. 
diagrs., tab. (NACA RM A53D06) 



THE RESULTS OF WIND-TUNNEL TESTS AT LOW 
SPEEDS OF A FOUR-ENGINE PROPELLER-DRIVEN 
AIRPLANE CONFIGURATION HAVING A WING WITH 
40 OF SWEEPBACK AND AN ASPECT RATIO OF 
10. George G. Edwards, Donald A. Buell, and 
Jerald K. Dickson. December 1953. 121p. diagrs., 
photo., tabs. (NACA RM A53I28) 



THE EFFECTS OF OPERATING PROPELLERS ON 
THE LONGITUDINAL CHARACTERISTICS AT HIGH 
SUBSONIC SPEEDS OF A FOUR-ENGINE TRACTOR 
AIRPLANE CONFIGURATION HAVING A WING 
WITH 40° OF SWEEPBACK AND AN ASPECT RATIO 
OF 10. Fred B. Sutton and Fred A. Demele. 
January 1954. 106p. diagrs., photo., 11 tabs. 
(NACA RM A53J23) 



EFFECTS OF OPERATING PROPELLERS ON THE 
WING-SURFACE PRESSURES OF A FOUR-ENGINE 
TRACTOR AIRPLANE CONFIGURATION HAVING A 
WING WITH 40° OF SWEEPBACK. Carl D. Kolbe 
and Frederick W. Boltz. April 1954. 133p. 
diagrs., photo., 19 tabs. (NACA RM A53L29) 



STATIC LONGITUDINAL STABILITY CHARACTER- 
ISTICS OF A COMPOSITE-PLAN-FORM WING 
MODEL INCLUDING SOME COMPARISONS WITH A 
45° SWEPTBACK WING AT TRANSONIC SPEEDS. 
Walter D. Wolhart. August 1954. 36p. diagrs., 
photo., tabs. (NACA RM L54F24) 



ANALYSIS OF WIND-TUNNEL TESTS AT LOW 
SPEEDS OF A FOUR-ENGINE PROPELLER- 
DRIVEN AIRPLANE CONFIGURATION HAVING A 
WING WITH 40° OF SWEEPBACK. George G. 
Edwards and Donald A. Buell. October 1954. 137p. 
diagrs., photos., 2 tabs. (NACA RM A54F14) 



application of wing-body theory - to drag 

REDUCTION AT LOW SUPERSONIC SPEEDS. 
Barrett S. Baldwin, Jr. , and Robert R. Dickey. 
January 1955. 42p. (NACA RM A54J19) 



(1.7.1.1.3) 

Tail-Wing and Fuselage 

LONGITUDINAL STABILITY CHARACTERISTICS OF 
A 42° SWEPTBACK WING AND TAIL COMBINATION 
AT A REYNOLDS NUMBER OF 6.8 x 10 6 . Stanley H. 
Spooner and Albert P. Martina. July 22, 1948. 
44p. diagrs., photos., 2 tabs. (NACA RM L8E12) 



LONGITUDINAL -STABILITY INVESTIGATION OF 
HIGH-LIFT AND STALL-CONTROL DEVICES ON A 
52° SWEPTBACK WING WITH AND WITHOUT FUSE- 
LAGE AND HORIZONTAL TAIL AT A REYNOLDS 
NUMBER OF 6.8 x 10 6 . Gerald V. Foster and 
James E. Fitzpatrick. December 20, 1948. 41p. 
diagrs., photos., tabs. (NACA RM L8I08) 



EFFECTS OF HIGH-LIFT AND STALL-CONTROL 
DEVICES, FUSELAGE, AND HORIZONTAL TAIL ON 
A WING SWEPT BACK 42° AT THE LEADING EDGE 
AND HAVING SYMMETRICAL CIRCULAR-ARC AIR- 
FOIL SECTIONS AT A REYNOLDS NUMBER OF 
6.9 x 10 6 . Robert L. Woods and Stanley H. 
Spooner. April 20, 1949, 42p. diagrs., photos., 
tabs. (NACA RM L9B11) 



WIND-TUNNEL INVESTIGATION OF A TAILLESS 
TRIANGULAR-WING FIGHTER AIRCRAFT AT 
MACH NUMBERS FROM 0.5 TO 1.5. Leslie F. 
Lawrence and James L. Summers. June 24, 1949. 
56p. diagrs., photos., tab. (NACA RM A9B16) 



76 



(1) AERODYNAMICS 



AERODYNAMIC STUDY OF A WING-FUSELAGE 
COMBINATION EMPLOYING A WING SWEPT BACK 
63°. - AERODYNAMIC CHARACTERISTICS IN 
SIDESLIP OF A LARGE-SCALE MODEL HAVING A 
63° SWEPT-BACK VERTICAL TAIL. Gerald M. 
McCormack. October 7, 1949. 26p. diagrs., 
photos. (NACA RM A9F14) 



A STUDY OF SEVERAL FACTORS AFFECTING THE 
STABILITY CONTRIBUTED BY A HORIZONTAL 
TAIL AT VARIOUS VERTICAL POSITIONS ON A 
SWEPTBACK-WING AIRPLANE MODEL. Gerald V. 
Foster and Roland F. Griner. October 28, 1949. 
28p. diagrs., tab. (NACA RM L9H19) 

INVESTIGATION OF A THIN WING OF ASPECT 
RATIO 4 IN THE AMES 12-FOOT PRESSURE WIND 
TUNNEL. V - STATIC LONGITUDINAL STABILITY 
AND CONTROL THROUGHOUT THE SUBSONIC 
SPEED RANGE OF A SEMISPAN MODEL OF A 
SUPERSONIC AIRPLANE. Ben H. Johnson, Jr. , 
and Francis W. Rollins. December 8, 1949. 130p. 
diagrs., photos. (NACA RM A9I01) 



HORIZONTAL-TAIL EFFECTIVENESS AND DOWN- 
WASH SURVEYS FOR TWO 47.7° SWEPTBACK 
WING-FUSELAGE COMBINATIONS WITH ASPECT 
RATIOS OF 5.1 AND 6.0 AT A REYNOLDS NUMBER 
OF 6.0 x lO**. Reino J. Salmi. January 12, 1951. 
65p. diagrs., photos., 2 tabs. (NACA RM L50K06) 



LOW-SPEED LONGITUDINAL AND WAKE AIR- 
FLOW CHARACTERISTICS AT A REYNOLDS NUM- 
BER OF 6.0 x 10 6 OF A 52° SWEPTBACK WING 
EQUIPPED WITH VARIOUS SPANS OF LEADING- 
EDGE AND TRAILING-EDGE FLAPS, A FUSELAGE, 
AND A HORIZONTAL TAIL AT VARIOUS VERTICAL 
POSITIONS. Roland F. Griner and Gerald V. Foster. 
February 28, 1951. 66p. diagrs., photo., 3 tabs. 
(NACA RM L50K29) 

TESTS IN THE AMES 40- BY 80-FOOT WIND TUN- 
NEL OF AN AIRPLANE CONFIGURATION WITH AN 
ASPECT RATIO 2 TRIANGULAR WING AND AN 
ALL-MOVABLE HORIZONTAL TAIL- 
LONGITUDINAL CHARACTERISTICS. David Graham 
and David G. Koenig. April 23, 1951. 35p. diagrs., 
photo., 3 tabs. (NACA RM A51B21) 

LOW-SPEED LONGITUDINAL AND WAKE AIR- 
FLOW CHARACTERISTICS AT A REYNOLDS NUM- 
BER OF 5.5 x 10 6 OF A CIRCULAR-ARC 52° 
SWEPTBACK WING WITH A FUSELAGE AND A 
HORIZONTAL TAIL AT VARIOUS VERTICAL POSI- 
TIONS. Gerald V. Foster and Roland F. Griner. 
June 19, 1951. 44p. diagrs., tabs. 
(NACA RM L51C30) 



TESTS IN THE AMES 40- BY 80-FOOT WIND TUN- 
NEL OF AN AIRPLANE CONFIGURATION WITH AN 
ASPECT RATIO 4 TRIANGULAR WING AND AN 
ALL-MOVABLE HORIZONTAL TAIL - LONGITUDI- 
NAL CHARACTERISTICS. David Graham and 
David G. Koenig. October 1951. 27p. diagrs., 
photo., 4 tabs. (NACA RM A51H10a) 



THE STATIC LONGITUDINAL CHARACTERISTICS 
AT MACH NUMBERS UP TO 0.95 OF A 
TRIANGULAR-WING CANARD MODEL HAVING A 
TRIANGULAR CONTROL. Jack D. Stephenson and 
Ralph Selan. December 1951. 72p. diagrs., photo. 
(NACA RM A51I07) 



EFFECT OF VERTICAL LOCATION OF A HORIZON- 
TAL TAIL ON THE STATIC LONGITUDINAL STA- 
BILITY CHARACTERISTICS OF A 45° SWEPTBACK- 
WING - FUSELAGE COMBINATION OF ASPECT 
RATIO 8 AT A REYNOLDS NUMBER OF 4.0 x 10 b . 
Relno J. Salmi and William A. Jacques. January 
1952. 42p. diagrs., photos. (NACA RM L51J08) 



TESTS IN THE AMES 40- BY 80-FOOT WIND TUN- 
NEL OF AN AIRPLANE CONFIGURATION WITH AN 
ASPECT RATIO 2 TRIANGULAR WING AND AN 
ALL-MOVABLE HORIZONTAL TAIL - LATERAL 
CHARACTERISTICS. David Graham and David G. 
Koenig. February 1952. 38p. diagrs., 2 tabs. 
(NACA RM A51L03) 



USE OF AN AERODYNAMICALLY PULSED ALL- 
MOVABLE HORIZONTAL TAIL TO OBTAIN LONGI- 
TUDINAL CHARACTERISTICS OF ROCKET- 
POWERED MODELS IN FREE FLIGHT AND SOME 
INITIAL RESULTS FROM AN ARROW -WING -BODY - 
TAIL CONFIGURATION. Warren Gillespie, Jr., and 
Albert E. Dietz. May 1952. 31p. diagrs., photos. 
(NACA RM L52C10) 

EFFECT OF CAMBER AND TWIST ON THE STA- 
BILITY CHARACTERISTICS OF MODELS HAVING A 
45° SWEPT WING AS DETERMINED BY THE FREE- 
FALL METHOD AT TRANSONIC SPEEDS. Maurice 
D. White. August 1952. 35p. diagrs., photos., tab. 
(NACA RMA52F16) 



LONGITUDINAL STABILITY, TRIM, AND DRAG 
CHARACTERISTICS OF A ROCKET-PROPELLED 
MODEL OF AN AIRPLANE CONFIGURATION HAV- 
ING A 45° SWEPTBACK WING AND AN UNSWEPT 
HORIZONTAL TAIL. James H. Parks and Alan B. 
Kehlet. August 1952. 29p. diagrs., photos., tab. 
(NACA RM L52F05) 



INVESTIGATION OF THE LOW-SPEED AERO- 
DYNAMIC CHARACTERISTICS OF A VARIABLE - 
SWEEP AIRPLANE MODEL WITH A WING HAVING 
PARTIAL-SPAN CAMBERED-LEADING-EDGE 
MODIFICATIONS. Robert E. Becht and Andrew L. 
Byrnes, Jr. September 1952. 47p. diagrs., photos. 
(NACA RM L52G08a) 



THE EFFECTS OF SWEEPBACK ON LONGITUDINAL 
CHARACTERISTICS OF A 1/30-SCALE SEMISPAN 
MODEL OF THE BELL X-5 AIRPLANE AS DETER- 
MINED FROM NACA WING -FLOW TESTS AT 
TRANSONIC SPEEDS. Joseph J. Kolnick and 
Robert M. Kennedy. November 1952. 48p. diagrs., 
photos., tab. (NACA RM L52I23) 



THE LONGITUDINAL CHARACTERISTICS AT MACH 
NUMBERS UP TO 0.9 OF A WING-FUSELAGE-TAIL 
COMBINATION HAVING A WING WITH 40° OF 
SWEEPBACK AND AN ASPECT RATIO OF 10. 
Bruce E. Tinling. December 1952. 41p. diagrs., 
photo., tab. (NACA RM A52I19) 



EFFECTS OF TWIST AND CAMBER, FENCES, AND 
HORIZONTAL-TAIL HEIGHT ON THE LOW-SPEED 
LONGITUDINAL STABILITY CHARACTERISTICS OF 
A WING- FUSELAGE COMBINATION WITH A 45° 
SWEPTBACK WING OF ASPECT RATIO 8 AT A 
REYNOLDS NUMBER OF 4.0 x 10 6 . Gerald V. 
Foster. December 1952. 30p. diagrs., photo. 
(NACA RM L52J03) 



77 



(1) AERODYNAMICS 



LONGITUDINAL-CONTROL EFFECTIVENESS AND 
DOWNWASH CHARACTERISTICS AT TRANSONIC 
SPEEDS OF A 1/30-SCALE SEMISPAN MODEL OF 
THE BELL X-5 AIRPLANE AS DETERMINED BY 
THE NACA WING-FLOW METHOD. Norman S. 
Silsby and Garland J. Morris. January 1953. 48p. 
diagrs., photos., 2 tabs. (NACA RM L52K12) 



TESTS IN THE AMES 40- BY 80-FOOT WIND TUN- 
NEL OF AN AIRPLANE MODEL WITH AN ASPECT 
RATIO 4 TRIANGULAR WING AND AN ALL- 
MOVABLE HORIZONTAL TAIL - HIGH -LIFT DE- 
VICES AND LATERAL CONTROLS. Ralph W. 
Franks. February 1953. 45p. diagrs., photo., 2 
tabs. (NACA RM A52K13) 



TESTS IN THE AMES 40- BY 80-FOOT WIND TUN- 
NEL OF TWO AIRPLANE MODELS HAVING AS- 
PECT RATIO 2 TRAPEZOIDAL WINGS OF TAPER 
RATIOS 0.33 AND 0.20. Ralph W. Franks. 
February 1953. 56p. diagrs., photos., 3 tabs. 
(NACA RM A52L16) 



LOW -SPEED LONGITUDINAL CHARACTERISTICS 
OF AN UNSWEPT HEXAGONAL WING WITH AND 
WITHOUT A FUSELAGE AND A HORIZONTAL TAIL 
LOCATED AT VARIOUS POSITIONS AT REYNOLDS 
NUMBERS FROM 2. 8 x 10 6 TO 7. 6 x 10 6 . Gerald 
V. Foster, Ernst F. Mollenberg and Robert L. 
Woods. February 26, 1953. 63p. diagrs., photos., 
3 tabs. (NACA RM L52LiIb) 



TESTS IN THE AMES 40- BY 80-FOOT WIND TUN- 
NEL OF AN AIRPLANE CONFIGURATION WITH AN 
ASPECT RATIO 3 TRIANGULAR WING AND AN 
ALL-MOVABLE HORIZONTAL TAIL - LONGITU- 
DINAL AND LATERAL CHARACTERISTICS. David 
G. Koenig. April 1953. 61p. diagrs., photos., 
4 tabs. (NACA RM A52L15) 



INVESTIGATION OF THE EFFECTS OF WING AND 
TAIL MODIFICATIONS ON THE LOW-SPEED STA- 
BILITY CHARACTERISTICS OF A MODEL HAVING 
A THIN 40° SWEPT WING OF ASPECT RATIO 3.5. 
Joseph Weil, William C. Sleeman, Jr., and Andrew 
L, Byrnes, Jr. April 1953. 95p. diagrs., photos., 
tab. (NACA RM L53C09) 



THE EFFECTS OF NACELLES AND OF EXTENDED 
SPLIT FLAPS ON THE LONGITUDINAL CHARAC- 
TERISTICS OF A WING-FUSELAGE-TAIL COMBI- 
NATION HAVING A WING WITH 40° OF SWEEP- 
BACK AND AN ASPECT RATIO OF 10. Bruce E. 
Tinling and Armando E. Lopez. June 1953. 47p. 
diagrs., tab. (NACA RM A53D06) 



THE LOW-SPEED LIFT AND DRAG CHARACTER- 
ISTICS OF A SERIES OF AIRPLANE MODELS 
HAVING TRIANGULAR OR MODIFIED TRIANGULAR 
WINGS. David Graham. June 1953. 49p. diagrs., 
photo., tabs. (NACA RM A53D14) 



TESTS IN THE AMES 40- BY 80-FOOT WIND TUN- 
NEL OF AN AIRPLANE CONFIGURATION WITH A 
VARIABLE-INCIDENCE TRIANGULAR WING AND 
AN ALL-MOVABLE HORIZONTAL TAIL. David G. 
Koenig. June 1953. 42p. diagrs., photo,, tabs. 
(NACA RM A53D21) 



INVESTIGATION AT LOW SPEED OF THE FLOW 
FIELD BEHIND THE LIFTING SURFACES OF A 
MODEL EQUIPPED WITH A 60° TRIANGULAR WING 
AND A 60° TRIANGULAR CANARD TAIL. Ernest E. 
Newman and Jones F. Cahill. June 1953. 44p. 
diagrs., photos., tab. (NACA RM L53C30) 



LONGITUDINAL STABILITY AND WAKE-FLOW 
CHARACTERISTICS OF A TWISTED AND 
CAMBERED WING-FUSELAGE COMBINATION OF 
45° SWEEPBACK AND ASPECT RATIO 8 WITH A 
HORIZONTAL TAIL AND STALL-CONTROL DE- 
VICES AT A REYNOLDS NUMBER OF 4.0 x 10 6 . 
Gerald V. Foster. June 1953. 51p. diagrs., 
photos., tab. (NACA RM L53D08) 

EFFECTS OF HORIZONTAL-TAIL HEIGHT AND A 
WING LEADING-EDGE MODIFICATION CON- 
SISTING OF A FULL-SPAN FLAP AND A PARTIAL- 
SPAN CHORD-EXTENSION ON THE AERODYNAMIC 
CHARACTERISTICS IN PITCH AT HIGH SUBSONIC 
SPEEDS OF A MODEL WITH A 45° SWEPTBACK 
WING. William D. Morrison, Jr. and William J. 
Alford, Jr. June 1953. 37p. diagrs., photo., tab. 
(NACA RM L53E06) 



WIND-TUNNEL INVESTIGATION TO DETERMINE 
THE HORIZONTAL- AND VERTICAL-TAIL CON- 
TRIBUTIONS TO THE STATIC LATERAL STABIL- 
ITY CHARACTERISTICS OF A COMPLETE -MODEL 
SWEPT -WING CONFIGURATION AT HIGH SUBSON- 
IC SPEEDS. James W. Wiggins, Richard E. Kuhn, 
and Paul G. Fournier. July 1953. 34p. diagrs., 
photo. (NACA RM L53E19) 



THE EFFECTS OF LEADING-EDGE EXTENSIONS, 
A TRAILING-EDGE EXTENSION, AND A FENCE 
ON THE STATIC LONGITUDINAL STABILITY OF A 
WING-FUSELAGE-TAIL COMBINATION HAVING 
A WING WITH 35° OF SWEEPBACK AND AN AS- 
PECT RATIO OF 4.5. Ralph Selan and Angelo 
Bandettini. August 1953. 81p. diagrs., photos., 
tabs. (NACA RM A53E12) 

FLIGHT MEASUREMENTS OF LIFT AND DRAG 
FOR THE BELL X-l RESEARCH AIRPLANE HAV- 
ING A 10-PERCENT-THICK WING. Edwin J. 
Saltzman. September 1953. 37p. diagrs., tab. 

(NACA RM L53F08) 



A TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE LONGITUDINAL STABILITY AND CONTROL 
CHARACTERISTICS OF A 0.09-SCALE MODEL OF 
THE BELL X-5 RESEARCH AIRPLANE AND COM- 
PARISON WITH FLIGHT. Ralph P. Bielat and 
George S. Campbell. October 1953. 65p. diagrs., 
photo. (NACA RM L53H18) 



FREE-FLIGHT-TUNNEL INVESTIGATION OF THE 
LOW-SPEED STABILITY AND CONTROL CHARAC- 
TERISTICS OF A CANARD AIRPLANE MODEL. 
Joseph L. Johnson, Jr., and John W. Paulson. 
October 1953. 37p. diagrs., photo., 2 tabs. (NACA 
RML53I11) 



THE RESULTS OF WIND-TUNNEL TESTS AT LOW 
SPEEDS OF A FOUR-ENGINE PROPELLER-DRIVEN 
AIRPLANE CONFIGURATION HAVING A WING WITH 
40° OF SWEEPBACK AND AN ASPECT RATIO OF 
10. George G. Edwards, Donald A. Buell, and 
Jerald K. Dickson. December 1953. 121p. diagrs., 
photo., tabs. (NACA RM A53I28) 



78 



(1) AERODYNAMICS 



WIND-TUNNEL INVESTIGATION AT LOW SPEED 
OF THE EFFECTS OF CHORDWISE WING FENCES 
AND HORIZONTAL-TAIL POSITION ON THE 
STATIC LONGITUDINAL STABILITY CHARACTER- 
ISTICS OF AN AIRPLANE MODEL WITH A 35° 
SWEPTBACK WING. M. J. Quetjo, Byron M. 
Jaquet, and Walter D. Wolhart. 1954. 11, 29p. 
diagrs., photos., tab. (NACA Rept. 1203. Super- 
sedes RM L50K07; RM L51H17) 



THE EFFECTS OF OPERATING PROPELLERS ON 
THE LONGITUDINAL CHARACTERISTICS AT HIGH 
SUBSONIC SPEEDS OF A FOUR-ENGINE TRACTOR 
AIRPLANE CONFIGURATION HAVING A WING 
WITH 40° OF SWEEPBACK AND AN ASPECT RATIO 
OF 10. Fred B. Sutton and Fred A. Demele. 
January 1954. 106p. diagrs., photo., 11 tabs. 
(NACA RM A53J23) 



STABILITY CHARACTERISTICS AT LOW SPEED OF 
A VARIABLE-SWEEP AIRPLANE MODEL HAVING 
A PARTIALLY CAMBERED WING WITH SEVERAL 
CHORD-EXTENSION CONFIGURATIONS. Robert E. 
Becht. February 1954. 37p. diagrs., photos. 
(NACA RM L53L14) 



THE EFFECTS OF HORIZONTAL -TAIL HEIGHT 
AND A PARTIAL-SPAN LEADING-EDGE EXTEN- 
SION ON THE STATIC LONGITUDINAL STABILITY 
OF A WING-FUSELAGE-TAIL COMBINATION 
HAVING A SWEPTBACK WING. Angelo Bandettini 
and Ralph Selan. March 1954. 54p. diagrs., 
photos., 2 tabs. (NACA RM A53J07) 



DISTRIBUTION OF LIFT AND PITCHING MOMENT 
BETWEEN WING AND FUSELAGE AND EFFECTS 
OF WING FLEXIBILITY AND DIVE BRAKE ON A 
1/30-SCALE SEMISPAN MODEL OF THE BELL X-5 
AIRPLANE AT TRANSONIC SPEEDS AS DETER- 
MINED BY THE NACA WING-FLOW METHOD. 
Garland J. Morris and Norman S. Silsby. March 
1954. 46p. diagrs., photos., tab. 
(NACARM L54A11) 



FLIGHT INVESTIGATION OF THE EFFECTS OF A 
PARTIAL-SPAN LEADING-EDGE CHORD EXTEN- 
SION OF THE AERODYNAMIC CHARACTERISTICS 
OF A 35° SWEPT -WING FIGHTER AIRPLANE. 
Frederick H. Matteson and Rudolph D, Van Dyke, Jr. 
April 1954. 34p. diagrs., photos., tabs. 
(NACA RM A54B26) 



LARGE-SCALE LOW-SPEED WIND-TUNNEL TESTS 
OF A MODEL HAVING A 60° DELTA HORIZONTAL 
CANARD CONTROL SURFACE AND WING TO OB- 
TAIN STATIC-LONGITUDINAL-STABILITY AND 
CANARD-SURFACE HINGE-MOMENT DATA. 
Dale L. Burrows. June 1954. 21p. diagrs. 
(NACA RM L54D16a) 



EFFECTS OF HIGH-LIFT DEVICES AND 
HORIZONTAL-TAIL LOCATION ON THE LOW- 
SPEED CHARACTERISTICS OF A LARGE-SCALE 
45° SWEPT-WING AIRPLANE CONFIGURATION. 
Ralph L. Maki and Ursel R. Embry. August 1954. 
46p. diagrs., photo., tabs. (NACA RM A54E10) 



STATIC LONGITUDINAL STABILITY CHARACTER- 
ISTICS OF A COMPOSITE-PLAN-FORM WING 
MODEL INCLUDING SOME COMPARISONS WITH A 
45° SWEPTBACK WING AT TRANSONIC SPEEDS. 
Walter D. Wolhart, August 1954. 36p. diagrs., 
photo., tabs. (NACA RM L54F24) 



ANALYSIS OF WIND-TUNNEL TESTS AT LOW 
SPEEDS OF A FOUR -ENGINE PROPELLER- 
DRIVEN AIRPLANE CONFIGURATION HAVING A 
WING WITH 40° OF SWEEPBACK. George G. 
Edwards and Donald A. Buell. October 1954. 137p. 
diagrs., photos., 2 tabs. (NACA RM A54F14) 



EFFECTS OF WING POSITION AND FUSELAGE 
SIZE ON THE LOW -SPEED STATIC AND ROLLING 
STABILITY CHARACTERISTICS OF A DELTA-WING 
MODEL. Alex Goodman and David F. Thomas, Jr. 
1955. ii, 31p. diagrs., photos., tabs. 
(NACA Rept. 1224. Supersedes TN 3063) 



A FLIGHT EVALUATION OF THE LONGITUDINAL 
STABILITY CHARACTERISTICS ASSOCIATED WITH 
THE PITCH-UP OF A SWEPT-WING AIRPLANE IN 
MANEUVERING FLIGHT AT TRANSONIC SPEEDS. 
Seth B. Anderson and Richard S. Bray. 1955. 11, 
12p. diagrs., photo., tab. (NACA Rept. 1237. 
Supersedes RM A51I12) 



WIND-TUNNEL INVESTIGATION AT LOW SPEED 
OF EFFECT OF SIZE AND POSITION OF CLOSED 
AIR DUCTS ON STATIC LONGITUDINAL AND 
STATIC LATERAL STABILITY CHARACTERISTICS 
OF UNSWEPT-MIDWING MODELS HAVING WINGS 
OF ASPECT RATIO 2, 4, AND 6. Byron M. Jaquet 
and James L. Williams. September 1955. 45p. 
diagrs., photos., tabs. (NACA TN 3481) 



VORTEX INTERFERENCE ON SLENDER AIR- 
PLANES. Alvin H. Sacks. November 1955. 19p. 
diagr. (NACA TN 3525) 



EXPERIMENTAL INVESTIGATION AT LOW SPEED 
OF EFFECTS OF FUSELAGE CROSS SECTION ON 
STATIC LONGITUDINAL AND LATERAL STABILITY 
CHARACTERISTICS OF MODELS HAVING 0° AND 
45° SWEPTBACK SURFACES. William Letko and 
James L. Williams. December 1955. 45p. diagrs., 
tabs. (NACA TN 3551) 



A PRELIMINARY INVESTIGATION OF THE EF- 
FECTS OF FREQUENCY AND AMPLITUDE ON THE 
ROLLING DERIVATIVES OF AN UNSWEPT-WING 
MODEL OSCILLATING IN ROLL. Lewis R. Fisher, 
Jacob H. Lichtenstein, and Katherlne D. Williams. 
January 1956. 29p. diagrs., photos. 
(NACA TN 3554) 



STATIC LONGITUDINAL AND LATERAL STABILITY 
CHARACTERISTICS AT LOW SPEED OF UNSWEPT- 
MIDWING MODELS HAVING WINGS WITH AN 
ASPECT RATIO OF 2, 4, OR 6. Walter D, Wolhart 
and David F. Thomas, Jr. May 1956. 41p. 
diagrs., photos., tabs. (NACA TN 3649) 



79 



(1) AERODYNAMICS 



(1.7. 1.1.4) 

Propeller and Jet Interference 



THE RESULTS OF WIND-TUNNEL TESTS AT LOW 
SPEEDS OF A FOUR-ENGINE PROPELLER -DRIVEN 
AIRPLANE CONFIGURATION HAVING A WING WITH 
40° OF SWEEPBACK AND AN ASPECT RATIO OF 
10. George G. Edwards, Donald A. Buell, and 
Jerald K. Dickson. December 1953. 121p. diagrs., 
photo., tabs. (NACA RM A53I28) 



THE EFFECTS OF OPERATING PROPELLERS ON 
THE LONGITUDINAL CHARACTERISTICS AT HIGH 
SUBSONIC SPEEDS OF A FOUR-ENGINE TRACTOR 
AIRPLANE CONFIGURATION HAVING A WING 
WITH 40° OF SWEEPBACK AND AN ASPECT RATIO 
OF 10. Fred B. Sutton and Fred A. Demele. 
January 1954. 106p. diagrs., photo., 11 tabs. 
(NACA RM A53J23) 



ANALYSIS OF WIND-TUNNEL TESTS AT LOW 
SPEEDS OF A FOUR-ENGINE PROPELLER- 
DRIVEN AIRPLANE CONFIGURATION HAVING A 
WING WITH 40° OF SWEEPBACK. George G. 
Edwards and Donald A. Buell. October 1954. 137p. 
diagrs., photos., 2 tabs. (NACA RM A54F14) 



(1.7.1. 1.5) 

External Stores 

EFFECT OF WING-TANK LOCATION ON THE DRAG 
AND TRIM OF A SWEPT -WING MODEL AS MEAS- 
URED IN FLIGHT AT TRANSONIC SPEEDS. 
Clement J. Welsh and John D. Morrow. April 4, 
1950. 18p. diagrs., photos. (NACA RM L50A19) 



EXPERIMENTAL INVESTIGATION OF VARIOUS 
WING-MOUNTED EXTERNAL STORES ON A WING- 
FUSELAGE COMBINATION HAVING A SWEPTBACK 
WING OF INVERSE TAPER RATIO. Kenneth P. 
Spreemann and H. Norman Silvers. September 15, 
1950. 29p. diagrs., photos., tab. (NACA RM L9J06) 



TRANSONIC FLIGHT TESTS TO COMPARE THE 
ZERO-LIFT DRAG OF UNDERSLUNG AND SYM- 
METRICAL NACELLES VARIED CHORDWISE AT 
40 PERCENT SEMISPAN OF A 45° SWEPTBACK, 
TAPERED WING. William B. Pepper, Jr., and 
Sherwood Hoffman. October 25, 1950. 36p. 
diagrs., photos., tabs. (NACA RM L50G17a) 



INVESTIGATION OF THE EFFECTS OF GEO- 
METRIC CHANGES IN AN UNDERWING PYLON - 
SUSPENDED EXTERNAL-STORE INSTALLATION 
ON THE AERODYNAMIC CHARACTERISTICS OF A 
45° SWEPTBACK WING AT HIGH SUBSONIC 
SPEEDS. Kenneth P. Spreemann and William J. 
Alford, Jr. March 5, 1951. 91p. diagrs., photos., 
tabs. (NACA RM L50L12) 



COMPARISON OF ZERO- LIFT DRAGS DETER- 
MINED BY FLIGHT TESTS AT TRANSONIC SPEEDS 
OF SYMMETRICALLY MOUNTED NACELLES IN 
VARIOUS SPANWISE POSITIONS ON A 45° SWEPT- 
BACK WING AND BODY COMBINATION. William B. 
Pepper, Jr., and Sherwood Hoffman. May 23, 1951. 
29p. diagrs., photos., tabs. (NACA RM L51D06) 



COMPARISON OF ZERO-LIFT DRAG DETERMINED 
BY FLIGHT TESTS AT TRANSONIC SPEEDS OF 
PYLON, UNDERSLUNG, AND SYMMETRICALLY 
MOUNTED NACELLES AT 40 PERCENT SEMISPAN 
OF A 45° SWEPTBACK WING AND BODY COMBINA- 
TION. Sherwood Hoffman. June 1951. 18p. diagrs., 
photos., tabs. (NACA RM L51D26) 



COMPARISON OF ZERO-LIFT DRAGS DETER- 
MINED BY FLIGHT TESTS AT TRANSONIC SPEEDS 
OF SYMMETRICALLY MOUNTED NACELLES IN 
VARIOUS CHORDWISE POSITIONS AT THE WING 
TIP OF A 45° SWEPTBACK WING AND BODY 
COMBINATION. William B. Pepper, Jr., and 
Sherwood Hoffman. September 1951. 16p. diagrs., 
photos. (NACA RM L51F13) 



INVESTIGATION OF THE EFFECT OF A NACELLE 
AT VARIOUS CHORDWISE AND VERTICAL POSI- 
TIONS ON THE AERODYNAMIC CHARACTERISTICS 
AT HIGH SUBSONIC SPEEDS OF A 45° SWEPTBACK 
WING WITH AND WITHOUT A FUSELAGE. 
H. Norman Silvers, Thomas J. King, Jr., and 
Thomas B. Pasteur, Jr. September 1951. 71p. 
diagrs., photos., 3 tabs. (NACA RM L51H16) 



TRANSONIC FLIGHT TESTS TO DETERMINE 
ZERO-LIFT DRAG AND PRESSURE RECOVERY OF 
NACELLES LOCATED AT THE WING TIPS ON A 
45° SWEPTBACK WING AND BODY COMBINATION. 
Sherwood Hoffman and William B. Pepper, Jr. 
January I»52. 21 p. diagrs., photos. , tabs. 
(NACA RM L51K02) 



TRANSONIC FLIGHT TESTS TO COMPARE THE 
ZERO-LIFT DRAGS OF 45° SWEPTBACK WINGS OF 
ASPECT RATIO 3.55 AND 6.0 WITH AND WITHOUT 
NACELLES AT THE WING TIPS. Sherwood Hoffman 
and Richard C. Mapp. Jr. March 1952. 17p. 
diagrs., photos. (NACA RM L51L27) 



TRANSONIC FLIGHT TESTS TO COMPARE THE 
ZERO-LIFT DRAGS OF UNDERSLUNG NACELLES 
VARIED SPANWISE ON A 45° SWEPTBACK WING 
AND BODY COMBINA TION. Sherwood Hoffman. 
July 1952. 16p. diagrs., photos. 
(NACA RM L52D04a) 



INVESTIGATION OF THE EFFECT OF CHORDWISE 
POSITIONING AND SHAPE OF AN UNDERWING NA- 
CELLE ON THE HIGH-SPEED AERODYNAMIC 
CHARACTERISTICS OF A 45° SWEPTBACK 
TAPERED-IN-THICKNESS-RATIO WING OF AS- 
PECT RATIO 6. H. Norman Stivers and Thomas J. 
King, Jr. January 1953. 50p. diagrs. 
(NACA RM L52K25) 



LOW-SPEED INVESTIGATION OF THE AERODY- 
NAMIC, CONTROL, AND HINGE-MOMENT CHAR- 
ACTERISTICS OF TWO TYPES OF CONTROLS ON 
A DELTA-WING-FUSELAGE MODEL WITH AND 
WITHOUT NACELLES. William I. Scallion. May 
1953. 47p. diagrs., photos., tabs. 
(NACA RM L53C18) 



SOME EFFECTS OF EXTERNAL WING TIP STORES 
ON THE ROLLING EFFECTIVENESS AND DRAG OF 
PLAIN AND HALF-DELTA TIP AILERONS ON A 
4-PERCENT-THICK, TAPERED, UNSWEPT WING. 
Roland D. English. August 1954, 14p, diagrs,, 
photos., tab. (NACA RM L54F29a) 



(1) AERODYNAMICS 



ARRANGEMENT OF FUSIFORM BODIES TO RE- 
DUCE THE WAVE DRAG AT SUPERSONIC SPEEDS. 
Morris D. Friedman and Doris Cohen. 1955. ii, 
8p. diagrs. (NACA Rept. 1236. Supersedes 
RM A51I20; TN 3345) 



APPLICATION OF WING-BODY THEORY TO DRAG 
REDUCTION AT LOW SUPERSONIC SPEEDS. 
Barrett S. Baldwin, Jr. , and Robert R. Dickey. 
January 1955. 42p. (NACA RM A54J19) 



PRELIMINARY STUDY OF SOME FACTORS WHICH 
AFFECT THE STALL-FLUTTER CHARACTER- 
ISTICS OF THIN WINGS. A. Gerald Rainey. March 
1956. 33p. diagrs., photo., tab. (NACA TN 3622. 
Supersedes RM L52D08) 



(1. 7. 1. 2) 
SPECIFIC AIRPLANES 



THE AERODYNAMIC EFFECTS OF ROCKETS AND 
FUEL TANKS MOUNTED UNDER THE SWEPT - 
BACK WING OF AN AIRPLANE MODEL. Lee E. 
Boddy and Charles P. Morrill, Jr. April 23. 1948. 
19p. diagrs. (NACA RM A7J03) 



MEASUREMENTS OF THE CHORDWISE PRESSURE 
DISTRIBUTIONS OVER THE WING OF THE XS-1 
RESEARCH AIRPLANE IN FLIGHT. De E. Beeler, 
Milton D. McLaughlin, and Dorothy C. Clift. 
August 4, 1948. 35p. diagrs., photo., tab. (NACA 
RM L8G21) 



PRELIMINARY RESULTS OF NACA TRANSONIC 
FLIGHTS OF THE XS-1 AIRPLANE WITH 10- 
PERCENT-THICK WING AND 8-PERCENT-THICK 
HORIZONTAL TAIL. Hubert M. Drake, Harold R. 
Goodman, and Herbert H. Hoover. October 13, 1948. 
18p. diagrs., photos. (NACA RM L8I29) 



EFFECTS OF A SWEPTBACK HYDROFOIL ON THE 
FORCE AND LONGITUDINAL STABILITY CHARAC- 
TERISTICS OF A TYPICAL HIGH-SPEED AIR- 
PLANE. Raymond B. Wood. December 2, 1948. 
19p. diagrs., photo., tabs. (NACA RM L8I30a) 



WIND-TUNNEL INVESTIGATION OF A TAILLESS 
TRIANGULAR-WING FIGHTER AIRCRAFT AT 
MACH NUMBERS FROM 0.5 TO 1.5. Leslie F. 
Lawrence and James L. Summers. June 24, 1949. 
56p. diagrs., photos., tab. (NACA RM A9B16) 



PRELIMINARY THEORETICAL AND FLIGHT IN- 
VESTIGATION OF THE LATERAL OSCILLATION 
OF THE X-l AIRPLANE. Hubert M. Drake and 
Helen L. Wall. July 19, 1949. 24p. diagrs., photo., 
tab. (NACA RM L9F07) 



MEASUREMENTS OF AILERON EFFECTIVENESS 
OF THE BELL X-l AIRPLANE AT MACH NUMBERS 
BETWEEN 0.9 AND 1.06. Hubert M, Drake. 
August 4, 1949. 5p. diagrs. (NACA RM L9G19a) 



LONGITUDINAL STABILITY AND CONTROL CHAR- 
ACTERISTICS OF A SEMISPAN WIND-TUNNEL 
MODEL OF A TAILLESS AIRPLANE AND A COM- 
PARISON WITH COMPLETE-MODEL WIND-TUNNEL 
TESTS AND SEMISPAN-MODEL WING-FLOW TESTS. 
Kenneth W. Goodson and Thomas J. King, Jr. 
October 10, 1949. 63p. diagrs., photos. 
(NACA RM L9C31) 



AERODYNAMIC CHARACTERISTICS AND FLYING 
QUALITIES OF A TAILLESS TRIANGULAR-WING 
AIRPLANE CONFIGURATION AS OBTAINED FROM 
FLIGHTS OF ROCKET-PROPELLED MODELS AT 
TRANSONIC AND LOW SUPERSONIC SPEEDS. 
Grady L. Mitcham, Joseph E. Stevens, and Harry P. 
Norris. February 9, 1950. 67p. diagrs., photos., 
tabs. (NACA RM L9L07) 



EXPERIMENTAL INVESTIGATION OF VARIOUS 
WING-MOUNTED EXTERNAL STORES ON A WING- 
FUSELAGE COMBINATION HAVING A SWEPTBACK 
WING OF INVERSE TAPER RATIO. Kenneth P. 
Spreemann and H. Norman Silvers. September 15, 
1950. 29p. diagrs., photos., tab. (NACA RM L9J06) 



ELEVATOR-STABILIZER EFFECTIVENESS AND 
TRIM OF THE X-l AIRPLANE TO A MACH NUM- 
BER OF 1.06. Hubert M. Drake and John R. Carden. 
November 1, 1950. 12p. diagrs. 
(NACA RM L50G20) 



PRELIMINARY FLIGHT INVESTIGATION OF THE 
MANEUVERING ACCELERATIONS AND BUFFET 
BOUNDARY OF A 35° SWEPT -ATNG AIRPLANE AT 
HIGH ALTITUDE AND TRANSONIC SPEEDS. 
George A. Rathert, Jr., Howard L. Ziff, and George 
E. Cooper. February 21, 1951. 12p. diagrs.. 
photo., tab. (NACA RM A50L04) 



REVIEW OF SOME RECENT DATA ON BUFFET 
BOUNDARIES. Paul E. Purser and John A. Wyss. 
May 23, 1951. lip. diagrs. (NACA RM L51E02a) 



TABULATED PRESSURE COEFFICIENTS AND 
AERODYNAMIC CHARACTERISTICS MEASURED 
ON THE WING OF THE BELL X-l AIRPLANE IN 

AN UNACCELERATED STALL AND IN PULL-UPS 
AT MACH NUMBERS OF 0.74, 0.75, 0.94, AND 
0.97. Lawrence A. Smith. June 19, 1951. 49p. 
diagrs., photo., tabs. (NACA RM L51B23) 



EFFECT OF FORMATION POSITION ON LOAD 
FACTORS OBTAINED ON F2H AIRPLANES. Carl R. 
Huss and Harold A. Hamer. December 1951. 15p. 
diagrs., 3 tabs. (NACA RM L51I05) 



FLIGHT CALIBRATION OF ANGLE-OF-ATTACK 
AND SIDESLIP DETECTORS ON THE FUSELAGE 
OF A 35° SWEPT -WING FIGHTER AIRPLANE. 
Norman M. McFadden, George A. Rathert, Jr., and 
Richard S. Bray. February 1952. 26p. diagrs., 
photos. (NACA RM A52A04) 



TIME HISTORIES OF MANEUVERS PERFORMED 
WITH AN F-86A AIRPLANE DURING SQUADRON 
OPERATIONS. Harold A. Hamer and Campbell 
Henderson. February 1952. 90p. diagrs., 3 tabs. 
(NACA RM L51K30) 



81 



( 1 ) AERODYNAMICS 



PRELIMINARY RESULTS OF HORIZONTAL -TAIL 
LOAD MEASUREMENTS OF THE BELL X-5 RE- 
SEARCH AIRPLANE. John T, Rogers and Angel H. 
Dunn. August 15, 1952. 22p. diagrs., photos., 
tabs. (NACA RM L52G14) 



A CORRELATION WITH FLIGHT TESTS OF RE- 
SULTS OBTAINED FROM THE MEASUREMENT OF 
WING PRESSURE DISTRIBUTIONS ON A 1/4-SCALE 
MODEL OF THE X-l AIRPLANE (10-PERCENT- 
THICK WING). Jack F. Runckel and James H. 
Henderson. September 1952. 60p. diagrs., photos., 
tab. (NACA RM L52E29) 



THE EFFECTS OF SWEEPBACK ON LONGITUDINAL 
CHARACTERISTICS OF A 1/30-SCALE SEMISPAN 
MODEL OF THE BELL X-5 AIRPLANE AS DETER- 
MINED FROM NACA WING-FLOW TESTS AT 
TRANSONIC SPEEDS. Joseph J. Kolnick and 
Robert M. Kennedy. November 1952. 48p. diagrs., 
photos., tab. (NACA RM L52I23) 



LONGITUDINAL-CONTROL EFFECTIVENESS AND 
DOWNWASH CHARACTERISTICS AT TRANSONIC 
SPEEDS OF A 1/30-SCALE SEMISPAN MODEL OF 
THE BELL X-5 AIRPLANE AS DETERMINED BY 
THE NACA WING-FLOW METHOD. Norman S. 
Silsby and Garland J. Morris. January 1953. 48p. 
diagrs,, phutos., 2 tabs. (NACA RM L52K12) 



FLIGHT MEASUREMENTS OF THE STABILITY 
CHARACTERISTICS OF THE BELL X-5 RESEARCH 
AIRPLANE IN SIDESLIPS AT 59° SWEEPBACK. 
Joan M. Childs. February 1953. 23p. diagrs., 
photos., tab. (NACA RM L52K13b) 



PRELIMINARY RESULTS OF STABILITY AND CON- 
TROL INVESTIGATION OF THE BELL X-5 RE- 
SEARCH AIRPLANE. Thomas W. Finch and Donald 
W. Briggs. February 1953. 35p. diagrs., photos., 
tabs. (NACA RM L52K18b) 



FLIGHT DETERMINATION OF THE STATIC LONGI- 
TUDINAL STABILITY BOUNDARIES OF THE BELL 
X-5 RESEARCH AIRPLANE WITH 59° SWEEPBACK, 
Thomas W. Finch and Joseph A. Walker. February 
1953. 51p. diagrs., photo., tab. 
{NACA RM L53A09b) 



LIFT AND DRAG CHARACTERISTICS OF THE 
BELL X-5 RESEARCH AIRPLANE AT 59° SWEEP- 
BACK FOR MACH NUMBERS FROM 0,60 TO 1.03. 
Donald R. Bellman. February 1953. 37p. diagrs., 
photos., tab. (NACA RM L53A09c) 



A FLIGHT COMPARISON OF A SUBMERGED INLET 
AND A SCOOP INLET AT TRANSONIC SPEEDS. 
L. Stewart Rolls. March 1953. 41p. diagrs., 
photo., tab. (NACA RM A53A06) 



COMPARISON OF MEASURED AND PREDICTED 
INDICATED ANGLES OF ATTACK NEAR THE 
FUSELAGES OF A TRIANGULAR-WING WIND- 
TUNNEL MODEL AND A SWEPT -WING FIGHTER 
AIRPLANE IN FLIGHT. Norman M. McFadden, 
John L. McCloud, III, and Harry A, James. 
March 1953. 13p. diagrs. (NACA RM A53A15) 



AILERON AND ELEVATOR HINGE MOMENTS OF 
THE BELL X-l AIRPLANE MEASURED IN TRAN- 
SONIC FLIGHT. Hubert M. Drake and John B. 
McKay. June 1953. 27p. diagrs. 
(NACA RM L53E04) 



THE EFFECTS OF FENCES ON THE HIGH-SPEED 
LONGITUDINAL STABILITY OF A SWEPT-WING 
AIRPLANE. Richard S. Bray. August 1953. 37p. 
diagrs., photos., tabs. (NACA RM A53F23) 



LONGITUDINAL FLIGHT CHARACTERISTICS OF 
THE BELL X-5 RESEARCH AIRPLANE AT 59° 
SWEEPBACK WITH MODIFIED WING ROOTS. 
James A. Martin. August 1953. 25p. diagrs., 
photos., tab. (NACA RM L53E28) 



FLIGHT MEASUREMENTS OF LIFT AND DRAG 
FOR THE BELL X-l RESEARCH AIRPLANE HAV- 
ING A 10-PERCENT-THICK WING. Edwin J. 
Saitzman. September 1953. 37p. diagrs., tab. 
(NACA RM L53F08) 



A TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE LONGITUDINAL STABILITY AND CONTROL 
CHARACTERISTICS OF A 0.09-SCALE MODEL OF 
THE BELL X-5 RESEARCH AIRPLANE AND COM- 
PARISON WITH FLIGHT. Ralph P. Bielat and 
George S. Campbell. October 1953. 65p. diagrs., 
photo. (NACA RM L53H18) 



SOME EFFECTS OF AEROELASTICITY AND 
SWEEPBACK ON THE ROLLING EFFECTIVENESS 
AND DRAG OF A 1/11-SCALE MODEL OF THE 
BELL X-5 AIRPLANE WING AT MACH NUMBERS 
*KOM 0.6 TO 1.5. Roland D. English. November 
1953. 21p. diagrs., photos. (NACA RM L53I18b) 



AN ANALYTICAL STUDY OF THE EFFECT OF 
AIRPLANE WAKE ON THE LATERAL DISPERSION 
OF AERIAL SPRAYS. Wilmer H. Reed, III. 1954. 
ii, 16p. diagrs., 3 tabs. (NACA Rept. 1196. 
Formerly TN 3032) 



DISTRIBUTION OF LIFT AND PITCHING MOMENT 
BETWEEN WING AND FUSELAGE AND EFFECTS 
OF WING FLEXIBILITY AND DIVE BRAKE ON A 
1/30-SCALE SEMISPAN MODEL OF THE BELL X-5 
AIRPLANE AT TRANSONIC SPEEDS AS DETER- 
MINED BY THE NACA WING-FLOW METHOD. 
Garland J. Morris and Norman S. Silsby. March 
1954. 4Gp. diagrs., photos., tab. 
(NACARM L54A11) 



FLIGHT INVESTIGATION OF THE EFFECTS OF A 
PARTIAL-SPAN LEADING-EDGE CHORD EXTEN- 
SION OF THE AERODYNAMIC CHARACTERISTICS 
OF A 35° SWEPT-WING FIGHTER AIRPLANE. 
Frederick H. Matteson and Rudolph D. Van Dyke, Jr. 
April 1954. 34p. diagrs., photos., tabs. 
(NACA RM A54B26) 



THE EFFECT OF BLUNT-TRAILING-EDGE MODI- 
FICATIONS ON THE HIGH-SPEED STABILITY AND 
CONTROL CHARACTERISTICS OF A SWEPT-WING 
FIGHTER AIRPLANE. Melvin Sadoff, Frederick H. 
Matteson, and Rudolph D. Van Dyke, Jr. May 1954. 
55p. diagrs., photos., tab. (NACA RM A54C31) 



82 



(1) AERODYNAMICS 



FLIGHT DETERMINATION OF THE BUFFETING 
CHARACTERISTICS OF THE BELL X-5 RESEARCH 
AIRPLANE AT 58.7° SWEEPBACK. Donald W. 
Briggs. May 1954. 31p. diagrs., photo., tabs. 
(NACARM L54C17) 



MEASUREMENT AND ANALYSIS OF WING AND 
TAIL BUFFETING LOADS ON A FIGHTER AIR- 
PLANE. Wilber B. Huston and T. H. Skopinski. 
1955. i, 27p. diagrs., photo., tabs. (NACA Rept. 
1219. Supersedes TN 3080) 



A FLIGHT EVALUATION OF THE LONGITUDINAL 
STABILITY CHARACTERISTICS ASSOCIATED WITH 
THE PITCH-UP OF A SWEPT -WING AIRPLANE IN 
MANEUVERING FLIGHT AT TRANSONIC SPEEDS. 
SethB. Anderson and Richard S. Bray. 1955. li, 
12p. diagrs., photo., tab. (NACA Rept. 1237. 
Supersedes RM A51I12) 



THE DYNAMIC-RESPONSE CHARACTERISTICS OF 
A 35° SWEPT-WING AIRPLANE AS DETERMINED 
FROM FLIGHT MEASUREMENTS. William C. 
Triplett, Stuart C. Brown, and G. Allan Smith. 
1955. ii, 25p. diagrs., tabs. (NACA Rept. 1250. 
Supersedes RM A51G27; RM A52I17) 



WING-LOAD MEASUREMENTS OF THE BELL X-5 
RESEARCH AIRPLANE AT A SWEEP ANGLE OF 
58.7°. Richard p. Banner, Robert D. Reed, and 
William L. Marcy. April 1955. 22p. diagrs., 
photo., tab. (NACA RM H55A11) 



FLIGHT DETERMINATION OF THE LONGITUDINAL 
STABILITY AND CONTROL CHARACTERISTICS OF 
THE BELL X-5 RESEARCH AIRPLANE AT 58.7° 
SWEEPBACK, Thomas W. Finch. May 1955. 30p. 
diagrs., photo., tab. (NACA RM H55C07) 



FLIGHT TESTS OF LEADING-EDGE AREA SUCTION 
ON A FIGHTER-TYPE AIRPLANE WITH A 35° 
SWEPTBACK WING. Richard S. Bray and Robert C. 
Innis. June 1955. 30p. diagrs., photos., tab. 
(NACA RM A55C07) 



FLIGHT MEASUREMENTS OF HORIZONTAL-TAIL 
LOADS ON THE BELL X-5 RESEARCH AIRPLANE 
AT A SWEEP ANGLE OF 58.7°. Robert D. Reed. 
July 1955. 19p. diagrs., photo., tab. 
(NACA RM H55E20a) 



A COMPARISON OF THE MEASURED AND PRE- 
DICTED LATERAL OSCILLATORY CHARACTERIS- 
TICS OF A 35° SvVEPT-WING FIGHTER AIRPLANE. 
Walter E. McNeill and George E. Cooper. August 
1955. 22p. diagrs., photo., 3 tabs. (NACA 
TN 3521. Formerly RM A51C28) 



ANALYSIS OF THE HORIZONTAL-TAIL LOADS 
MEASURED IN FLIGHT ON A MULTIENGINE JET 
BOMBER. William S. Aiken, Jr. and Bernard 
Wiener. September 1955. i, 69p. diagrs., photo., 
6 tabs. (NACA TN 3479) 



THE EFFECTIVENESS OF WING VORTEX GENERA- 
TORS IN IMPROVING THE MANEUVERING CHARAC- 
TERISTICS OF A SWEPT-WING AIRPLANE AT 
TRANSONIC SPEEDS. Norman M. McFadden, 
George A. Rathert, Jr., and Richard S. Bray. 
September 1955. 43p. diagrs. , photos. , tab. 
(NACA TN 3523. Supersedes RM A51J18) 



FLIGHT MEASUREMENTS OF THE DYNAMIC 
LATERAL AND LONGITUDINAL STABILITY OF 
THE BELL X-5 RESEARCH AIRPLANE AT 58.7° 
SWEEPBACK. Edward N. Videan. October 1955. 
68p. diagrs., photo., tabs. (NACA RM H55H10) 



FLIGHT CALIBRATION OF FOUR AIRSPEED SYS- 
TEMS ON A SWEPT-WING AIRPLANE AT MACH 
NUMBERS UP TO 1.04 BY THE NACA RADAR- 
PHOTOTHEODOLITE METHOD. Jim Rogers 
Thompson, Richard S. Bray, and George E. Cooper. 
November 1955. 41p. diagrs., photos., tab. 
(NACA TN 3526. Supersedes RM A50H24) 



A WIND-TUNNEL INVESTIGATION OF A 0.4-SCALE 
MODEL OF AN ASSAULT-TRANSPORT AIRPLANE 
WITH BOUNDARY-LAYER CONTROL APPLIED. 

Marvin P. Fink, Bennie W. Cocke, and Stanley 
Lipson. May 1956. 63p. diagrs., photos. 
(NACA RM L55G26a) 



INVESTIGATION OF LATERAL CONTROL NEAR 
THE STALL. FLIGHT TESTS WITH HIGH-WING 
AND LOW-WING MONOPLANES OF VARIOUS CON- 
FIGURATIONS. Fred E. Weick and H. Norman 
Abramson, Agricultural and Mechanical College of 
Texas. June 1956. 34p. diagrs., photos., tabs. 
(NACA TN 3676) 



INVESTIGATION OF LATERAL CONTROL NEAR 
THE STALL. ANALYSIS FOR REQUIRED LONGI- 
TUDINAL TRIM CHARACTERISTICS AND DISCUS- 
SION OF DESIGN VARIABLES. Fred E. Weick and 
H. Norman Abramson, Agricultural and Mechanical 
College of Texas. June 1956. 91p. diagrs., tabs. 
(NACA TN3677) 



(1.7. 1. 3) 
PERFORMANCE 



TIME HISTORIES OF MANEUVERS PERFORMED 
WITH AN F-86A AIRPLANE DURING SQUADRON 
OPERATIONS. Harold A. Hamer and Campbell 
Henderson. February 1952. 90p. diagrs., 3 tabs. 

(NACA RM L51K30) 



TECHNIQUES FOR DETERMINING THRUST IN 
FLIGHT FOR AIRPLANES EQUIPPED WITH 
AFTERBURNERS. L. Stewart Rolls, C. Dewey 
Havill, and George R. Holden. January 1953. 27p. 
diagrs., photos. (NACA RM A52K12) 



A FLIGHT INVESTIGATION OF THE EFFECT OF 
LEADING-EDGE CAMBER ON THE AERODYNAMIC 
CHARACTERISTICS OF A SWEPT-WING AIRPLANE. 
Seth B. Anderson, Frederick H. Matteson, and 
Rudolph D, Van Dyke, Jr. February 1953. 23p. 
diagrs., photos., tab. (NACA RM A52L16a) 



83 



(1) AERODYNAMICS 



LIFT AND DRAG CHARACTERISTICS OF THE 
BELL X-5 RESEARCH AIRPLANE AT 59° SWEEP- 

BACK FOR MACH NUMBERS FROM 0.60 TO 1.03. 
Donald R. Bellman. February 1953. 37p. diagrs., 
photos., tab. (NACA RM L53A09c) 



A FLIGHT COMPARISON OF A SUBMERGED INLET 
AND A SCOOP INLET AT TRANSONIC SPEEDS. 
L. Stewart Rolls. March 1953. 41p. diagrs., 
photo., tab. (NACA RM A53A06) 



THE EFFECTS OF FENCES ON THE HIGH-SPEED 
LONGITUDINAL STABILITY OF A SWEPT-WING 
AIRPLANE. RichardS. Bray. August 1953. 37p. 
diagrs., photos., tabs. (NACA RM A53F23) 



THEORETICAL AND EXPERIMENTAL INVESTIGA- 
TION OF ADDITIVE DRAG. Merwin Sibulkin. 1954. 
ii, 12p. diagrs. (NACA Kept. 1187. Formerly 
RM E51B13) 



THE EFFECT OF BLUNT-TRAILING-EDGE MODI- 
FICATIONS ON THE HIGH-SPEED STABILITY AND 
CONTROL CHARACTERISTICS OF A SWEPT-WING 
FIGHTER AIRPLANE, Melvin Sadoff, Frederick H. 
Matteson, and Rudolph D. Van Dyke, Jr. May 1954. 
55p. diagrs., photos., tab. (NACA RM A54C31) 



OPTIMUM FLIGHT PATHS OF TURBOJET AIR- 
CRAFT. (Traiettorie Ottime Di Volo Degli Aero- 
plani Azionati Da Turboreattori). Angelo Miele. 
September 1955. 47p. diagrs. , tabs. (NACA TM 
1389. Trans, from L'Aerotecnica, v. 32, no. 4, 
1952, p. 206-219) 



THE EFFECTIVENESS OF WING VORTEX GENERA- 
TORS IN IMPROVING THE MANEUVERING CHARAC- 
TERISTICS OF A SWEPT-WING AIRPLANE AT 
TRANSONIC SPEEDS. Norman M. McFadden, 
George A. Rathert, Jr., and Richard S. Bray. 
September 1955. 43p. diagrs., photos., tab. 
(NACA TN 3523. Supersedes RM A51J18) 

GENERAL SOLUTIONS OF OPTIMUM PROBLEMS 
IN NONSTATIONARY FLIGHT. (Soluzioni General! 
di Problemi di Ottimo in Volo Non-Stazionario). 
Angelo Miele. October 1955. 25p. diagrs., tab. 
{NACA TM 1388. Trans, from L'Aerotecnica, v. 32, 
no. 3, 1952, p.135-142) 



MINIMUM WAVE DRAG FOR ARBITRARY AR- 
RANGEMENTS OF WINGS AND BODIES. Robert T, 
Jones. February 1956. lip. diagrs. 
(NACA TN 3530) 



INVESTIGATION OF THE EFFECTS OF GROUND 
PROXIMITY AND PROPELLER POSITION ON THE 
EFFECTIVENESS OF A WING WITH LARGE-CHORD 
SLOTTED FLAPS IN REDIRECTING PROPELLER 
SLIPSTREAMS DOWNWARD FOR VERTICAL TAKE- 
OFF. Richard E. Kuhn. March 1956. 38p. 
diagrs., photos., tab. (NACA TN 3629) 



INVESTIGATION AT ZERO FORWARD SPEED OF A 
LEADING-EDGE SLAT AS A LONGITUDINAL CON- 
TROL DEVICE FOR VERTICALLY RISING AIR- 
PLANES THAT UTILIZE THE REDIRECTED- 
SLIPST D EAM PRINCIPLE. Richard E. Kuhn. 
May 1956. 33p. diagrs., photos. (NACA TN 3692) 



PRELIMINARY INVESTIGATION OF THE EFFEC- 
TIVENESS OF A SLIDING FLAP IN DEFLECTING A 
PROPELLER SLIPSTREAM DOWNWARD FOR 
VERTICAL TAKE-OFF. Richard E. Kuhn and 
Kenneth P. Spreemann. May 1956. 25p. diagrs., 
photo. (NACA TN 3693) 



A SONIC -FLOW ORIFICE PROBE FOR THE IN- 
FLIGHT MEASUREMENT OF TEMPERATURE 
PROFILES OF A JET ENGINE EXHAUST WITH 
AFTERBURNING. C. Dewey Havill and L. Stewart 
Rolls. May 1956. 18p. diagrs., photos. 
(NACA TN 3714) 



(1.7.2) 
MISSILES 



SUMMARY OF FLUTTER EXPERIENCES AS A 
GUIDE TO THE PRELIMINARY DESIGN OF LIFTING 
SURFACES ON MISSILES. Dennis J. Martin. 
November 1951. 16p. diagrs. (NACA RM L51J30) 

A UNIFIED TWO-DIMENSIONAL APPROACH TO 
THE CALCULATION OF THREE-DIMENSIONAL 
HYPERSONIC FLOWS, WITH APPLICATION TO 
BODIES OF REVOLUTION. A. J. Eggers, Jr. and 
Raymond C. Savin. 1955. ii, 27p. diagrs., tab. 
(NACA Rept. 1249. Supersedes TN 2811) 

IMPINGEMENT OF WATER DROPLETS ON A 
SPHERE. Robert G. Dorsch, Paul G. Saper, and 



v.Kr.1. 1QRR 



tab. (NACA TN 3587) 



RESULTS OF A FLIGHT INVESTIGATION TO DE- 
TERMINE THE ZERO-LIFT DRAG CHARACTER- 
ISTICS OF A 60° DELTA WING WITH NACA 65-006 
AIRFOIL SECTION AND VARIOUS DOUBLE-WEDGE 
SECTIONS AT MACH NUMBERS FROM 0.7 TO 1.6. 
Clement J. Welsh. April 1956. 13p. diagrs., 
photo. (NACA TN 3650. Supersedes RM L50F01) 



(1.7. 2. 1) 

COMPONENTS IN COMBINATION 

LARGE-SCALE FLIGHT MEASUREMENTS OF 
ZERO-LIFT DRAG AT MACH NUMBERS FROM 
0.86 TO 1.5 OF A WING-BODY COMBINATION 
HAVING A 60° TRIANGULAR WING WITH NACA 
85A003 SECTIONS. Robert L. Nelson. June 1, 
1950. lOp. diagrs., photos., tab. 
(NACA RM L50D26) 



FLIGHT INVESTIGATION OF A ROLL-STABILIZED 
MISSILE CONFIGURATION AT VARYING ANGLES 
OF ATTACK AT MACH NUMBERS BETWEEN 0.8 
AND 1.79. Jacob Zarovsky and Robert A. Gardiner. 
March 6, 1951. 38p. diagrs., photos., tab. 
(NACARM L50H21) 

LARGE-SCALE FLIGHT MEASUREMENTS OF 
ZERO- LIFT DRAG AT MACH NUMBERS FROM 0.8 
TO 1.6 OF A WING- BODY COMBINATION HAVING 
AN UNSWEPT 4.5-PERCENT-THICK WING WITH 
MODIFIED HEXAGONAL SECTIONS. Eugene D. 
Schult. March 23, 1951. 14p. diagrs., photos., tab. 
(NACA RM L51A15) 

DOWNWASH AND SIDEWASH FIELDS BEHIND 
CRUCIFORM WINGS. John R. Spreiter. January 
1952. 18p. photos., diagrs. (NACA RM A51L17) 



84 



(1) AERODYNAMICS 



FLIGHT MEASUREMENTS AT MACH NUMBERS 
FROM 1.1 TO 1.9 OF THE ZERO-LIFT DRAG OF A 
TWIN-ENGINE SUPERSONIC RAM-JET CONFIGU- 
RATION. Abraham Leiss. June 1952. 16p. 
diagrs., photos. (NACA RM L52D24) 



LARGE-SCALE FLIGHT MEASUREMENTS OF 
ZERO-LIFT DRAG AND LOW-LIFT LONGITUDINAL 
CHARACTERISTICS OF A DIAMOND-WING— BODY 
COMBINATION AT MACH NUMBERS FROM 0.725 
TO 1.54. Harvey A. Wallskog and John D. Morrow. 
April 1953. 18p. diagrs., photo., tab. 
(NACA RM L53C17) 



THEORY OF WING-BODY DRAG AT SUPERSONIC 
SPEEDS. Robert T. Jones. September 1953, lip. 
diagrs. (NACA RM A53H18a) 



INVESTIGATION OF A CANARD MISSILE CON- 
FIGURATION (NACA RM-4) IN THE LANGLEY 
9-INCH SUPERSONIC TUNNEL AT MACH 
NUMBERS OF 1.62 AND 1.93. Carl E. Grigsby. 
June 1954. 24p. diagrs., photo. 
(NACA RM L54E20) 



THE WAVE DRAG OF ARBITRARY CONFIGURA- 
TIONS IN LINEARIZED FLOW AS DETERMINED 
BY AREAS AND FORCES IN OBLIQUE PLANES. 
Harvard Lorn ax. March 1955. 16p. 
(NACA RMA55A18) 



A SPECIAL METHOD FOR FINDING BODY DISTOR- 
TIONS THAT REDUCE THE WAVE DRAG OF WING 
AND BODY COMBINATIONS AT SUPERSONIC 
SPEEDS. Harvard Lomax and Max. A. Heaslet. 
May 1955. 113p. diagrs., tab. (NACA RM A55B16) 



GENERAL THEORY OF WAVE-DRAG REDUCTION 
FOR COMBINATIONS EMPLOYING QUASI- 
CYLINDRICAL BODIES WITH AN APPLICATION TO 
SWEPT -WING AND BODY COMBINATIONS. Jack 
N. Nielsen. June 1955. 74p. diagrs. 
(NACA RMA55B07) 



WING -BODY COMBINATIONS WITH CERTAIN GEO- 
METRIC RESTRAINTS HAVING LOW ZERO-LIFT 
WAVE DRAG AT LOW SUPERSONIC MACH NUM- 
BERS. Harvard Lomax. February 1956. 32p. 
diagrs. (NACA TN 3667) 



(1.7.2. 1. 1) 
Wing-Body 



LARGE-SCALE FLIGHT MEASUREMENTS OF 
ZERO- LIFT DRAG AT MACH NUMBERS FROM 
0.86 TO 1.5 OF A WING -BODY COMBINATION 
HAVING A 60° TRIANGULAR WING WITH NACA 
65A003 SECTIONS. Robert L. Nelson. June 1, 
1950. lOp. diagrs., photos., tab. 
(NACA RM L50D26) 

LIFT AND PITCHING-MOMENT INTERFERENCE 
BETWEEN A POINTED CYLINDRICAL BODY AND 
TRIANGULAR WINGS OF VARIOUS ASPECT RATIOS 
AT MACH NUMBERS OF 1.50 AND 2.02. Jack N. 
Nielsen, Elliott D. Katzen, and Kenneth K. Tang. 
September 12, 1950. 53p. diagrs., photos., tabs. 
(NACA RM A50F06) 



LARGE-SCALE FLIGHT MEASUREMENTS OF 
ZERO-LIFT DRAG AT MACH NUMBERS FROM 0.8 
TO 1.6 OF A WING- BODY COMBINATION HAVING 
AN UNSWEPT 4.5-PERCENT-THICK WING WITH 
MODIFIED HEXAGONAL SECTIONS. Eugene D. 
Schult. March 23, 1951. 14p. diagrs., photos., tab. 
(NACA RM L51A15) 



DRAG INTERFERENCE BETWEEN A POINTED 
CYLINDRICAL BODY AND TRIANGULAR WINGS OF 
VARIOUS ASPECT RATIOS AT MACH NUMBERS OF 
1.50 AND 2.02. Elliott D. Katzen and George E. 
Kaattari. May 23, 1951. 45p. diagrs., photos., tabs. 
(NACA RM A51C27) 



THE EFFECT ON ZERO-LIFT DRAG OF AN IN- 
DENTED FUSELAGE OR A THICKENED WING -ROOT 
MODIFICATION TO A 45° SWEPTBACK WING-BODY 
CONFIGURATION AS DETERMINED BY FLIGHT 
TESTS AT TRANSONIC SPEEDS. William B- 
Pepper. September 1951. 20p. diagrs., photos., 
2 tabs. (NACA RM L51F15) 



SOME EFFECTS OF FUSELAGE INTERFERENCE, 
WING INTERFERENCE AND SWEEPBACK ON THE 
DAMPING IN ROLL OF UNTAPEREi. /INGS AS DE- 
TERMINED BY TECHNIQUES EMPLOYING 
ROCKET-PROPELLED VEHICLES. William M. 
Bland, Jr., and Albert E. Dietz. October 1951. 27p. 
diagrs., photos. (NACA RM L51D25) 

DAMPING IN ROLL OF STRAIGHT AND 45° SWEPT 
WINGS OF VARIOUS TAPER RATIOS DETERMINED 
AT HIGH SUBSONIC, TRANSONIC, AND SUPER- 
SONIC SPEEDS WITH ROCKET-POWERED 
MODELS. E. Claude Sanders, Jr. October 1951. 
15p. diagrs. (NACA RM L51H14) 

DAMPING IN ROLL OF MODELS WITH 45°, 60°, 
AND 70° DELTA WINGS DETERMINED AT HIGH 
SUBSONIC, TRANSONIC, AND SUPERSONIC 
SPEEDS WITH ROCKET-POWERED MODELS. 
E. Claude Sanders, Jr. June 1952. 18p. diagrs., 
photos. (NACA RM L52D22a) 

EFFECT OF FUSELAGE INTERFERENCE ON THE 
DAMPING IN ROLL OF DELTA WINGS OF ASPECT 
RATIO 4 IN THE MACH NUMBER RANGE BETWEEN 
0.6 AND 1.6 AS DETERMINED WITH ROCKET- 
PROPELLED VEHICLES. William M. Bland, Jr. 
July 1952. 13p. diagrs., photos. (NACA RM L52E13) 



THE EFFECTS OF FUSELAGE SIZE ON THE LOW- 
SPEED LONGITUDINAL AERODYNAMIC CHARAC- 
TERISTICS OF A THIN 60° DELTA WING WITH 
AND WITHOUT A DOUBLE SLOTTED FLAP. John 
M. Riebe. February 1953. 24p. diagrs., photo., 
tab. (NACA RM L52L29a) 



LARGE-SCALE FLIGHT MEASUREMENTS OF 
ZERO-LIFT DRAG AND LOW-LIFT LONGITUDINAL 
CHARACTERISTICS OF A DIAMOND-WING— BODY 
COMBINATION AT MACH NUMBERS FROM 0.725 
TO 1.54. Harvey A. Wallskog and John D. Morrow. 
April 1953. 18p. diagrs., photo., tab 
(NACA RM L53C17) 



EXPERIMENTAL INVESTIGATION OF THE EF- 
FECTS OF PLAN-FORM TAPER ON THE AERO- 
DYNAMIC CHARACTERISTICS OF SYMMETRICAL 
UNSWEPT WINGS OF VARYING ASPECT RATIO. 
Edwin C. Allen. May 1953. 53p. diagrs., photos., 
tab. (NACA RM A53C19) 



85 



WIND-TUNNEL INVESTIGATION AT LOW SPEED 
OF THE EFFECT OF VARYING THE RATIO OF 
BODY DIAMETER TO WING SPAN FROM 0.1 TO 0.8 
ON THE AERODYNAMIC CHARACTERISTICS IN 
PITCH OF A 45° SWEPTBACK-WING— BODY 
COMBINATION. Harold S. Johnson. November 
1953. 32p. diagrs.. photo., tab. 
(NACA RM L53J09a) 



INVESTIGATION OF A CANARD MISSILE CON- 
FIGURATION (NACA RM-4) IN THE LANGLEY 
9 -INCH SUPERSONIC TUNNEL AT MACH 
NUMBERS OF 1.62 AND 1.93. Carl E. Grigsby. 
June 1954. 24p. diagrs., photo. 
(NACA RML54E20) 



DOWNWASH SURVEY BEHIND TWO LOW-ASPECT- 
RATIO VARIABLE-INCIDENCE WINGS IN COMBI- 
NATION WITH THREE DIFFERENT SIZE FUSE- 
LAGES AT A MACH NUMBER OF 0.25. Edward J. 
Hopkins and Norman E. Sorensen. March 1955. 54p. 
diagrs., photos., tab. (NACA RM A55A07) 



GENERAL THEORY OF WAVE -DRAG REDUCTION 
FOR COMBINATIONS EMPLOYING QUASI- 
CYLINDRICAL BODIES WITH AN APPLICATION TO 
SWEPT-WING AND BODY COMBINATIONS. Jack 
N. Nielsen. June 1955. 74p. diagrs. 
{NACA RM A55B07) 



FLIGHT INVESTIGATION AT MACH NUMBERS 
FROM 0.6 TO 1.7 TO DETERMINE DRAG AND 
BASE PRESSURES ON A BLUNT-TRAILING-EDGE 
AIRFOIL AND DRAG OF DIAMOND AND CIRCULAR- 
ARC AIRFOILS AT ZERO LIFT. John D. Morrow 
and Ellis Katz. November 1955. 19p. diagrs., 
photos. (NACA TN 3548. Supersedes RM LSOElSa) 



MEASUREMENTS OF THE EFFECT OF TRAILING- 
EDGE THICKNESS ON THE ZERO-LIFT DRAG OF 
THIN LOW-ASPECT-RATIO WINGS. John D. 
Morrow. November 1955. lip. diagrs., photo. 
(NACA TN 3550. Supersedes RM L50F26) 



A THEORETICAL STUDY OF THE AERODYNAMICS 
OF SLENDER CRUCIFORM-WING ARRANGEMENTS 
AND THEIR WAKES. John R. Spreiter and Alvin H. 
Sacks. March 1956. i, 67p. diagrs., photos., tabs. 
(NACA TN 3528) 



REDUCTION OF WAVE DRAG OF WING-BODY 
COMBINATIONS AT SUPERSONIC SPEEDS 
THROUGH BODY DISTORTIONS. William C, Pitts. 
April 1956. 9p. diagrs. (NACA RM A56B10) 



THEORETICAL PRESSURE DISTRIBUTIONS FOR 
SOME SLENDER WING-BODY COMBINATIONS AT 
ZERO LIFT. Paul F. Byrd. April 1956. 39p. 
diagrs. (NACA TN 3674. Supersedes RM A54J07) 



COMPARISON BETWEEN EXPERIMENTAL AND 
PREDICTED DOWNWASH AT A MACH NUMBER OF 
0.25 BEHIND A WING-BODY COMBINATION HAVING 
A TRIANGULAR WING OF ASPECT RATIO 2.0. 
Norman E. Sorensen and Edward J. Hopkins. May 
1956. 29p. diagrs., photos. (NACA TN 3720) 



(1) AERODYNAMICS 



(1.7.2. 1.2) 
Tail-Body 



FLIGHT INVESTIGATIONS AT HIGH -SUBSONIC, 
TRANSONIC, AND SUPERSONIC SPEEDS TO DE- 
TERMINE ZERO-LIFT DRAG OF FIN-STABILIZED 
BODIES OF REVOLUTION HAVING FINENESS 
RATIOS OF 12.5, 8.91, AND 6.04 AND VARYING 
POSITIONS OF MAXIMUM DIAMETER. Roger G. 
Hart and Ellis R. Katz. November 30, 1949. 36p. 
diagrs., photos. (NACA RM L9I30) 



LARGE-SCALE FLIGHT MEASUREMENTS OF 
ZERO- LIFT DRAG AT MACH NUMBERS FROM 
0.86 TO 1.5 OF A WING -BODY COMBINATION 
HAVING A 60° TRIANGULAR WING WITH NACA 
65A003 SECTIONS. Robert L. Nelson. June 1, 
1950. lOp. diagrs., photos., tab. 
(NACA RM L50D26) 



AERODYNAMIC CHARACTERISTICS OF NACA RM- 

10 MISSILE IN 8- BY 6-FOOT SUPERSONIC WIND 
TUNNEL AT MACH NUMBERS FROM 1.49 TO 1.98. 

11 - PRESENTATION AND ANALYSIS OF FORCE 
MEASUREMENTS. Fred T. Esenwein, Leonard J. 
Obery, and Carl F. Schueller. July 21, 1950. 34p 
diagrs., photo. (NACA RM E50D28) 



PRESSURE MEASUREMENTS ON A SHARPLY CON- 
VERGING FUSELAGE AFTERBODY WITH JET ON 
AND OFF AT MACH NUMBERS FROM 0.8 TO 1.6. 
William E. Stoney, Jr., and Ellis Katz. August 10, 
1950. 18p. diagrs., photos. (NACA RM L50F06) 

LARGE-SCALE FLIGHT MEASUREMENTS OF 
ZERO-LIFT DRAG AT MACH NUMBERS FROM 0.8 
TO 1.6 OF A WING- BODY COMBINATION HAVING 
AN UNSWEPT 4.5-PERCENT-THICK WING WITH 
MODIFIED HEXAGONAL SECTIONS. Eugene D. 
Schult. March 23, 1951. 14p. diagrs., photos., tab. 
(NACARM L51A15) 



AERODYNAMIC CHARACTERISTICS OF THE NACA 
RM-10 RESEARCH MISSILE IN THE AMES 1- BY 
3 -FOOT SUPERSONIC WIND TUNNEL NO. 2 - 
PRESSURE AND FORCE MEASUREMENTS AT 
MACH NUMBERS OF 1.52 AND 1.98. Edward W. 
Perkins, Forrest E. Go wen and Leland H. Jorgensen. 
September 1951. 37p. diagrs. (NACA RM A51G13) 

PRESSURE DISTRIBUTIONS AT MACH NUMBERS 
FROM 0.6 TO 1.9 MEASURED IN FREE FLIGHT ON 
A PARABOLIC BODY OF REVOLUTION WITH 
SHARPLY CONVERGENT AFTERBODY. William E. 
Stoney, Jr. April 1952. 34p. diagrs., photos. 
(NACARM L51L03) 

EFFECT OF CAMBER AND TWIST ON THE STA- 
BILITY CHARACTERISTICS OF MODELS HAVING A 
45° SWEPT WING AS DETERMINED BY THE FREE- 
FALL METHOD AT TRANSONIC SPEEDS. Maurice 
D. White. August 1952. 35p. diagrs., photos., tab. 
(NACA RM A52F16) 



EFFECTS OF STABILIZING FINS AND A REAR- 
SUPPORT STING ON THE BASE PRESSURES OF A 
BODY OF REVOLUTION IN FREE FLIGHT AT 
MACH NUMBERS FROM 0.7 TO 1.3. Roger G. 
Hart. September 1952. 19p. diagrs., photos., tab. 
{NACA RM L52E06) 



86 



(1) AERODYNAMICS 



INVESTIGATION OF THE AERODYNAMIC CHARAC- 
TERISTICS OF THE NACA RM-10 MISSILE (WITH 
FINS) AT A MACH NUMBER OF 1.62 IN THE 
LANGLEY 9-INCH SUPERSONIC TUNNEL. Donald 
E. Coletti. December 1952. 21p. diagrs. 
(NACA RML52J23a) 



LARGE-SCALE FLIGHT MEASUREMENTS OF 
ZERO -LIFT DRAG AND LOW -LIFT LONGITUDINAL 
CHARACTERISTICS OF A DIAMOND-WING— BODY 
COMBINATION AT MACH NUMBERS FROM 0.725 
TO 1.54. Harvey A. Wallskog and John D. Morrow. 
April 1953. 18p. diagrs., photo., tab. 
{NACA RM L53C17) 

AN EXPERIMENTAL AND THEORETICAL INVES- 
TIGATION AT HIGH SUBSONIC SPEEDS OF THE 
EFFECTS OF HORIZONTAL-TAIL HEIGHT ON THE 
AERODYNAMIC CHARACTERISTICS IN SIDESLIP 
OF AN UNSWEPT, UNTAPERED TAIL ASSEMBLY. 
Harleth G. Wiley and Donald R. Riley. December 
1953. 71p. diagrs., tab. (NACA RM L53J19) 



LONGITUDINAL STABILITY AND DRAG CHAR- 
ACTERISTICS OF A FIN-STABILIZED BODY OF 
REVOLUTION WITH A FINENESS RATIO OF 12 AS 
MEASURED BY THE FREE-FALL METHOD. 
Max C. Kurbjun. June 1954. 19p. diagrs., photos., 
tab. (NACA RM L54E13) 

INVESTIGATION OF A CANARD MISSILE CON- 
FIGURATION (NACA RM-4) IN THE LANGLEY 
9-INCH SUPERSONIC TUNNEL AT MACH 
NUMBERS OF 1.62 AND 1.93. Carl E. Grigsby. 
June 1954. 24p. djagrs., photo. 
(NACA RM L54E20) 



AN INVESTIGATION OF THE CHARACTERISTICS OF 
THE NACA RM-10 (WITH AND WITHOUT FINS) IN 
THE LANGLEY 11-INCH HYPERSONIC TUNNEL AT 
A MACH NUMBER OF 6.9. William D. McCauley 
and William V. Feller. November 1954. 37p. 
diagrs., photos. (NACA RM L54I03) 



(1. 7. 2. 1. 3) 

Jet Interference 



AERODYNAMIC INVESTIGATION OF A PARABOLIC 
BODY OF REVOLUTION AT MACH NUMBER OF 
1.92 AND SOME EFFECTS OF AN ANNULAR JET 
EXHAUSTING FROM THE BASE. Eugene S. Love. 
Februarys, 1950. 75p. diagrs., photos., tab 
(NACA RM L9K09) 



PRESSURE MEASUREMENTS ON A SHARPLY CON- 
VERGING FUSELAGE AFTERBODY WITH JET ON 
AND OFF AT MACH NUMBERS FROM 0.8 TO 1.6. 
William E. Stoney, Jr., and Ellis Katz. August 10, 
1950. 18p. diagrs., photos. (NACA RM L50F06) 



PRELIMINARY INVESTIGATION OF EFFECTIVE- 
NESS OF BASE BLEED IN REDUCING DRAG OF 
BLUNT-BASE BODIES IN SUPERSONIC STREAM. 
Edgar M. Cortright, Jr., and Albert H. Schroeder. 
March 9, 1951. 23p. diagrs., photos. 
(NACA RM E51A26) 



(1. 7. 2. 1.4) 
Wing-Tail-Body 

INVESTIGATION OF A THIN WING OF ASPECT 
RATIO 4 IN THE AMES 12-FOOT PRESSURE WIND 
TUNNEL. V - STATIC LONGITUDINAL STABILITY 
AND CONTROL THROUGHOUT THE SUBSONIC 
SPEED RANGE OF A SEMISPAN MODEL OF A 
SUPERSONIC AIRPLANE. Ben H. Johnson, Jr. , 
and Francis W. Rollins. December 8, 1949. 130p. 
diagrs., photos. (NACA RM A9I01) 

THE STATIC LONGITUDINAL CHARACTERISTICS 
AT MACH NUMBERS UP TO 0.95 OF A 
TRIANGULAR-WING CANARD MODEL HAVING A 
TRIANGULAR CONTROL. Jack D. Stephenson and 
Ralph Selan. December 1951. 72p. diagrs., photo. 
(NACA RM A51I07) 



EFFECT OF CAMBER AND TWIST ON THE STA- 
BILITY CHARACTERISTICS OF MODELS HAVING A 
45° SWEPT WING AS DETERMINED BY THE FREE- 
FALL METHOD AT TRANSONIC SPEEDS. Maurice 
D. White. August 1952. 35p. diagrs., photos., tab. 
(NACA RM A52F16) 

LONGITUDINAL STABILITY AND CONTROL CHAR- 
ACTERISTICS OF A CANARD MISSILE CONFIGURA- 
TION FOR MACH NUMBERS FROM 1.1 TO 1.93 AS 
DETERMINED FROM FREE-FLIGHT AND WIND- 
TUNNEL INVESTIGATIONS. Howard J. Curfman, 
Jr., and Carl E. Grigsby. August 1952. 28p. 
diagrs., tab. (NACA RM L52F06) 



INVESTIGATION OF A CANARD MISSILE CON- 
FIGURATION (NACA RM-4) IN THE LANGLEY 
9-INCH SUPERSONIC TUNNEL AT MACH 
NUMBERS OF 1.62 AND 1.93. Carl E. Grigsby. 
June 1954. 24p. diagrs., photo. 
(NACA RM L54E20) 

VORTEX INTERFERENCE ON SLENDER AIR- 
PLANES. Alvin H. Sacks. November 1955. 19p. 
diagr. (NACA TN 3525) 



DETERMINATION OF VORTEX PATHS BY SERIES 
EXPANSION TECHNIQUE WITH APPLICATION TO 
CRUCIFORM WINGS. Alberta Y. Alksne. 
April 1956. 40p. diagrs., photos. (NACA TN 3670) 



(1.7.2.2) 
SPECIFIC MISSILES 

FREE-FLIGHT INVESTIGATION OF CONTROL EF- 
FECTIVENESS OF FULL-SPAN, 0.2-CHORD PLAIN 
AILERONS AT HIGH SUBSONIC, TRANSONIC, AND 
SUPERSONIC SPEEDS TO DETERMINE SOME EF- 
FECTS OF WING SWEEPBACK, TAPER, ASPECT 
RATIO, AND SECTION-THICKNESS RATIO. Carl A. 
Sandahl. August 13, 1947. 16p. diagrs., photos., 
tab. (NACA RM L7F30) 

LOW-SPEED WIND-TUNNEL TESTS OF A PILOT- 
LESS AIRCRAFT HAVING HORIZONTAL AND 
VERTICAL WINGS AND CRUCIFORM TAIL. 
N. Mastrocola and A. Assadourian. August 19, 
1947. lOOp. diagrs., photos., tab. 
(NACA RM L6J18a) 



87 



(1) AERODYNAMICS 



THE LONGITUDINAL STABILITY, CONTROL EF- 
FECTIVENESS, AND CONTROL HINGE-MOMENT 
CHARACTERISTICS OBTAINED FROM A FLIGHT 
INVESTIGATION OF A CANARD MISSILE CONFIG- 
URATION AT TRANSONIC AND SUPERSONIC 
SPEEDS. Roy J. Niewald and Martin T. Moul. 
November 24, 1950. 43p. diagrs., photos. 
(NACA RM L50I27) 

LONGITUDINAL STABILITY AND CONTROL CHAR- 
ACTERISTICS FROM A FLIGHT INVESTIGATION 
OF A CRUCIFORM CANARD MISSILE CONFIGURA- 
TION HAVING AN EXPOSED WING-CANARD AREA 
RATIO OF 16:1. Martin T. Moul and Andrew R. 
Wineman. June 1952. 32p. diagrs., photos. 
(NACA RM L52D24a) 



LONGITUDINAL STABILITY AND CONTROL CHAR- 
ACTERISTICS OF A CANARD MISSILE CONFIGURA- 
TION FOR MACH NUMBERS FROM 1.1 TO 1.93 AS 
DETERMINED FROM FREE-FLIGHT AND WIND- 
TUNNEL INVESTIGATIONS. Howard J. Curfman, 
Jr., and Carl E. Grigsby! August 1952. 28p. 
diagrs., tab. (NACA RM L52F06) 



INVESTIGATION OF THE AERODYNAMIC CHARAC- 
TERISTICS OF THE NACA RM-10 MISSILE (WITH 
FINS) AT A MACH NUMBER OF 1.62 IN THE 
LANGLEY 9-INCH SUPERSONIC TUNNEL. Donald 
E. Colettk December ia&2_ 21p. diagrs. 
(NACA RM L52J23a) 

DRAG AND HEAT TRANSFER ON A PARABOLIC 
BODY OF REVOLUTION (NACA RM-10) IN FREE 
FLIGHT TO MACH'NUMBER 2 WITH BOTH CON- 
STANT AND VARYING REYNOLDS NUMBER AND 
HEATING EFFECTS ON TURBULENT SKIN FRIC- 
TION. Joseph P. Maloney. June 1954. 34p. 
diagrs., photo. (NACA RM L54D06) 



INVESTIGATION OF A CANARD MISSILE CON- 
FIGURATION (NACA RM-4) IN THE LANGLEY 
9-INCH SUPERSONIC TUNNEL AT MACH 
NUMBERS OF 1.62 AND 1.93. Carl E. Grigsby. 
June 1954. 24p. diagrs., photo. 
(NACA RM L54E20) 



AN INVESTIGATION OF THE CHARACTERISTICS OF 
THE NACA RM-10 (WITH AND WITHOUT FINS) IN 
THE LANGLEY 11-INCH HYPERSONIC TUNNEL AT 
A MACH NUMBER OF 6.9. William D. McCauley 
and William V. Feller. November 1954. 37p. 
diagrs., photos. (NACA RM L54I03) 



CORRELATION OF SUPERSONIC CONVECTIVE 
HEAT -TRANSFER COEFFICIENTS FROM MEAS- 
UREMENTS OF THE SKIN TEMPERATURE OF A 
PARABOLIC BODY OF REVOLUTION (NACA RM-10); 
Leo T. Chauvin and Carlos A. deMoraes. March 
1956. 38p. diagrs., photo., tabs. (NACA TN 3623. 
Supersedes RM L51A18) 



(1.7.3) 
ROTATING-WING AIRCRAFT 

SIMPLIFIED PROCEDURES AND CHARTS FOR THE 
RAPID ESTIMATION OF BENDING FREQUENCES 
OF ROTATING BEAMS. Robert T. Yntema. June 
1955. ii, 90p. diagrs., 6 tabs. (NACA TN 3459. 
Supersedes and extends RM L54G02) 



PERFORMANCE ANALYSIS OF FKED- AND FREE- 
TURBINE HELICOPTER ENGINES. Richard P. 
Krebs and William S. Miller, Jr. June 1956. 49p. 
diagrs. (NACA TN 3654) 



(1,7.3. 1) 
AUTOGIROS 



SUPPLEMENTARY CHARTS FOR ESTIMATING 
PERFORMANCE OF HIGH-PERFORMANCE HELI- 
COPTERS. Robert J. Tapscott and Alfred Gessow. 
July 1955. 31p. diagrs. (NaCA TN 3482) 

CHARTS FOR ESTIMATING ROTOR-BLADE FLAP- 
PING MOTION OF HIGH-PERFORMANCE HELICOP- 
TERS. Robert J. Tapscott and Alfred Gessow. 
March 1956. 19p. diagrs. (NACA TN 3616) 



(1.7.3.2) 
HELICOPTERS 



STUDIES OF THE SPEED STABnJTY OF A TAN- 
DEM HELICOPTER IN FORWARD FLIGHT. Robert 
J. Tapscott and Kenneth B. Amer. August 1953. 
35p. diagrs., photos., tab. (NACA RM L53F15a) 

THE NORMAL COMPONENT OF THE INDUCED 
VELOCITY IN THE VICINITY OF A LIFTING ROTOR 
AND SOME EXAMPLES OF ITS APPLICATION. 
Walter Castles, Jr. and Jacob Henri De Leeuw, 
Georgia Institute of Technology. 1954. ii, 15p. 
diagrs., 3 tabs. (NACA Rept. 1184. Formerly 
TN 2912) 

THEORETICAL AND EXPERIMENTAL INVESTIGA- 
TION OF MUFFLERS WITH COMMENTS ON 
ENGINE-EXHAUST MUFFLER DESIGN. Don D. 
Davis, Jr., George M. Stokes, Dewey Moore, and 
George L. Stevens, Jr. 1954. iv, 47p. diagrs., 
photos., tabs. (NACA Rept. 1192. Supersedes 
TN 2893; TN 2943) 



METHOD FOR STUDYING HELICOPTER LONGITU- 
DINAL MANEUVER STABILITY. Kenneth B. Amer. 
1954, ii, 17p. diagrs., photos., tabs. 
(NACA Rept. 1200. Supersedes TN 3022) 

STUDIES OF THE LATERAL -DIRECTIONAL FLY- 
ING QUALITIES OF A TANDEM HELICOPTER IN 
FORWARD FLIGHT. Kenneth B. Amer and Robert 
J. Tapscott. 1954. ii, 15p. diagrs., photos., tab. 
(NACA Rept. 1207. Supersedes TN 2984) 



INVESTIGATION OF A PULSE-JET-POWERED 
HELICOPTER ROTOR ON THE LANGLEY HELI- 
COPTER TEST TOWER. Edward J. Radin and 
Paul J. Carpenter. February 1954. 23p. diagrs., 
photos. (NACA RM L53L15) 



METHODS FOR OBTAINING DESIRED HELICOPTER 
STABILITY CHARACTERISTICS. F. B. Gustafson 
and Robert J. Tapscott. August 1954. 12p. tabs. 
(NACA RM L54F30) 



METHODS OF PREDICTING HELICOPTER STABIL- 
ITY. Robert J. Tapscott and F. B. Gustafson. 
November 1954. 15p. diagrs. (NACA RM L54G05) 



88 



(1) AERODYNAMICS 



CHARTS FOR ESTIMATING TAIL-ROTOR CONTRI- 
BUTION TO HELICOPTER DIRECTIONAL STABIL- 
ITY AND CONTROL IN LOW-SPEED FLIGHT. 
Kenneth B. Amer and Alfred Gessow. 1955. ii, 
22p. diagrs., photo., tabs. (NACA Rept. 1216. 
Supersedes TN 3156) 



SUPPLEMENTARY CHARTS FOR ESTIMATING 
PERFORMANCE OF HIGH-PERFORMANCE HELI- 
COPTERS. Robert J. Tapscott and Alfred Gessow. 
July 1955. 31p. diagrs. (NaCA TN 3482) 



GUST-TUNNEL INVESTIGATION OF THE EFFECT 
OF A SHARP -EDGE GUST ON THE FLAPWISE 
BLADE BENDING MOMENTS OF A MODEL HELI- 
COPTER ROTOR. Domenic J. Maglieri and Thomas 
D. Reisert. August 1955. 24p. diagrs., photos. 
(NACA TN 3470) 



NOTE ON HOVERING TURNS WITH TANDEM 
HELICOPTERS. John P. Reeder and Robert J. 
Tapscott. September 1955. 5p. photo. (NACA 
RM L55G21) 



HELICOPTER INSTRUMENT FLIGHT AND PRECI- 
SION MANEUVERS AS AFFECTED BY CHANGES IN 
DAMPING IN ROLL, PITCH, AND YAW. James B. 
Whitten, John P. Reeder, and Aimer D. Crim. 
November 1955. 14p. diagrs., photos. 
(NACA TN 3537) 



INVESTIGATION OF THE PROPULSP7E CHARAC- 
TERISTICS OF A HELICOPTER-TYPE PULSE-JET 
ENGINE OVER A RANGE OF MACH NUMBERS AND 
ANGLE OF YAW. Paul J. Carpenter, James P. 
Shivers, and Edwin E. Lee, Jr. January 1956. 
24p. diagrs., photos, (NACA TN 3625) 



EFFECT OF TRANSVERSE BODY FORCE ON CHAN- 
NEL FLOW WITH SMALL HEAT ADDITION. Simon 
Ostrach and Franklin K. Moore. February 1956. 
31p. diagrs. (NACA TN 3594) 

CHARTS FOR ESTIMATING ROTOR-BLADE FLAP- 
PING MOTION OF HIGH-PERFORMANCE HELICOP- 
TERS. Robert J. Tapscott and Alfred Gessow. 
March 1956. 19p. diagrs. (NACA TN 3616) 



WIND-TUNNEL INVESTIGATION OF EFFECTS OF 
FUSELAGE CROSS-SECTIONAL SHAPE, FUSE- 
LAGE BEND, AND VERTICAL-TAIL SIZE ON DI- 
RECTIONAL CHARACTERISTICS OF 
NONOVERLAP-TYPE HELICOPTER FUSELAGE 
MODELS WITHOUT ROTORS. James L. Williams. 
March 1956. 39p. diagrs., photos. 
(NACA TN 3645) 

NORMAL COMPONENT OF INDUCED VELOCITY IN 
THE VICINITY OF A LIFTING ROTOR WITH A NON- 
UNIFORM DISK LOADING. Harry H. Heyson and 
S. Katzoff. April 1956. i, 45p. diagrs. 
(NACA TN 3690) 



ANALYSIS AND-COMPARISON WITH THEORY OF 
FLOW-FIELD MEASUREMENTS NEAR A LIFTING 
ROTOR IN THE LANGLEY FULL-SCALE TUNNEL. 
Harry H. Heyson. April 1956. 162p. diagrs., 
photos., tab. (NACA TN 3691) 



(1.7.6) 
Bl -PLANES AND TRI- 



PLANES 



PRELIMINARY INVESTIGATION AT SUBSONIC AND 
TRANSONIC SPEEDS OF THE AERODYNAMIC 
CHARACTERISTICS OF A BIPLANE COMPOSED OF 
A SWEPTBACK AND A SWEPT FORWARD WING 
JOINED AT THE TIPS. Jones F. Can ill and 
Dexter H. Stead. March 1954. 19p. diagrs., 
photos. (NACA RM L53L24b) 



89 



(1) AERODYNAMICS 



(1.8) 
Stability and Control 



SOME FACTORS AFFECTING AUTOMATIC CON- 
TROL OF AIRPLANES. Charles W. Mathews. 
February 1952. 15p. diagrs. (NACA RM L52A30) 



STUDIES OF THE SPEED STABILITY OF A TAN- 
DEM HELICOPTER IN FORWARD FLIGHT.. Robert 
J. Tapscott and Kenneth B. Amer. August 1953. 
35p. diagrs., photos., tab. (NACA RM L53F15a) 



METHOD FOR STUDYING HELICOPTER LONGITU- 
DINAL MANEUVER STABILITY. Kenneth B. Amer. 
1954, ii, 17p. diagrs., photos., tabs. 
(NACA Rept. 1200. Supersedes TN 3022) 



STUDIES OF THE LATERAL-DIRECTIONAL FLY- 
ING QUALITIES OF A TANDEM HELICOPTER IN 
FORWARD FLIGHT. Kenneth B. Amer and Robert 
J. Tapscott. 1954. ii, 15p. diagrs., photos., tab. 
(NACA Rept. 1207. Supersedes TN 2984) 



METHODS FOR OBTAINING DESIRED HELICOPTER 
STABILITY CHARACTERISTICS. F. B. Gustafson 
and Robert J. Tapscott. August 1954. 12p. tabs. 
(NACA RM L54F30) 



METHODS OF PREDICTING HELICOPTER STABIL- 
ITY. Robert J. Tapscott and F. B. Gustafson. 

November 1954. 15p. diagrs. (NACA RM LG4G05) 



HELICOPTER INSTRUMENT FLIGHT AND PRECI- 
SION MANEUVERS AS AFFECTED BY CHANGES IN 
DAMPING IN ROLL, PITCH, AND YAW. James B. 
Whitten, John P. Reeder, and Aimer D. Crim. 
November 1955. 14p, diagrs., photos. 
(NACA TN 3537) 



(1.8.1) 
STABILITY 



VORTEX INTERFERENCE ON SLENDER AIR- 
PLANES. Alvin H. Sacks. November 1955. 19p. 
diagr. (NACA TN 3525) 



ACOUSTIC ANALYSIS OF RAM-JET BUZZ. Harold 
Mirels. November 1955. 33p diagrs. 
(NACA TN 3574) 



(1.8. 1. 1) 

STATIC 

DOWNWASH AND SIDEWASH FIELDS BEHIND 
CRUCIFORM WINGS. John R. Spreiter. January 
1952. 18p. photos., diagrs. (NACA RM A51L17) 



EFFECTS OF STABILIZING FINS AND A REAR- 
SUPPORT STING ON THE BASE PRESSURES OF A 
BODY OF REVOLUTION IN FREE FLIGHT AT 
MACH NUMBERS FROM 0.7 TO 1.3. Roger G. 
Hart. September 1952. 19p. diagrs., photos., tab. 
'NACA RM L52E06) 



LARGE-SCALE LOW-SPEED WIND-TUNNEL TESTS 
OF A MODEL HAVING A 60° DELTA HORIZONTAL 
CANARD CONTROL SURFACE AND WING TO OB- 
TAIN STATIC -LONGITUDINAL -STABILITY AND 
CANARD-SURFACE HINGE-MOMENT DATA. 
Dale L. Burrows. June 1954. 21p. diagrs. 
(NACA RM L54D16a) 



(1.8. 1. 1. 1) 
Longitudinal 



LOW -SPEED WIND-TUNNEL TESTS OF A PILOT - 
LESS AIRCRAFT HAVING HORIZONTAL AND 
VERTICAL WINGS AND CRUCIFORM TAIL. 
N. Mastrocola and A. Assadourian. August 19, 
1947. lOOp. diagrs., photos., tab. 
(NACA RM L6J18a) 



THE HIGH-SPEED AERODYNAMIC EFFECTS OF 
MODIFICATIONS TO THE WING AND WING- > 
FUSELAGE INTERSECTION OF AN AIRPLANE 
MODEL WITH THE WING SWEPT BACK 35°, Lee 
E. Boddy and Charles P, Morrill, Jr. February 18, 
1948. 34p. diagrs., photos. (NACA RM A7J02) 



HIGH-SPEED STABILITY AND CONTROL CHARAC- 
TERISTICS OF A FIGHTER AIRPLANE MODEL 
WITH A SWEPT-BACK WING AND TAIL. Charles 
P. Morrill, Jr., and Lee E. Boddy. April 14, 1948. 
47p. diagrs., photos. (NACA RM A7K28) 



THE AERODYNAMIC EFFECTS OF ROCKETS AND 
FUEL TANKS MOUNTED UNDER THE SWEPT- 
BACK WING OF AN AIRPLANE MODEL. Lee E. 
Boddy and Charles P. Morrill, Jr. April 23. 1948. 
19p. diagrs. (NACA RM A7J03) 



LONGITUDINAL STABILITY CHARACTERISTICS OF 
A 42° SWEPTBACK WING AND TAIL COMBINATION 
AT A REYNOLDS NUMBER OF 6.8 x 10 6 . Stanley H. 
Spooner and Albert P. Martina. July 22, 1948. 
44p. diagrs., photos., 2 tabs. (NACA RM L8E12) 



PRELIMINARY RESULTS OF NACA TRANSONIC 
FLIGHTS OF THE XS-1 AIRPLANE WITH 10- 
PERCENT-THICK WING AND 8-PERCENT-THICK 
HORIZONTAL TAIL. Hubert M. Drake, Harold R. 
Goodman, and Herbert H. Hoover. October 13, 1948. 
18p. diagrs., photos. (NACA RM L8I29) 



90 



(1) AERODYNAMICS 



EFFECTS OF A SWEPTBACK HYDROFOIL ON THE 
FORCE AND LONGITUDINAL STABILITY CHARAC- 
TERISTICS OF A TYPICAL HIGH-SPEED AIR- 
PLANE. Raymond B. Wood. December 2, 1948. 
19p. diagrs., photo., tabs. (NACA RM L8I30a) 



LONGITUDINAL-STABILITY INVESTIGATION OF 
HIGH-LIFT AND STALL-CONTROL DEVICES ON A 
52° SWEPTBACK WING WITH AND WITHOUT FUSE- 
LAGE AND HORIZONTAL TAIL AT A REYNOLDS 
NUMBER OF 6.8 x 10 6 . Gerald V^ Foster and 
James E. Fitzpatrick. December 20, 1948. 41p. 
diagrs., photos., tabs. (NACA RM L8I08) 



INVESTIGATION AT A MACH NUMBER OF 1.9 AND 
A REYNOLDS NUMBER OF 2.2 x 10 6 OF SEVERAL 
FLAP-TYPE LATERAL-CONTROL DEVICES ON A 
WING HAVING 42.7° SWEEPBACK OF THE LEAD- 
ING EDGE. Kennith L. Goin. March 11, 1949. 
28p. diagrs., photos., tabs. (NACA RM L9A18a) 



EFFECTS OF HIGH-LIFT AND STALL-CONTROL 
DEVICES, FUSELAGE, AND HORIZONTAL TAIL ON 
A WING SWEPT BACK 42° AT THE LEADING EDGE 
AND HAVING SYMMETRICAL CIRCULAR-ARC AIR- 
FOIL SECTIONS AT A REYNOLDS NUMBER OF 
6.9 x 10 6 . Robert L. Woods and Stanley H. 
Spooner. April 20, 1949. 42p. diagrs., photos., 
tabs. (NACA RM L9B11) 



LONGITUDINAL STABILITY AND CONTROL CHAR- 
ACTERISTICS OF A SEMISPAN WIND-TUNNEL 
MODEL OF A TAILLESS AIRPLANE AND A COM- 
PARISON WITH COMPLETE -MODEL WIND-TUNNEL 
TESTS AND SEMISPAN-MODEL WING-FLOW TESTS. 
Kenneth W. Goodson and Thomas J. King, Jr. 
October 10, 1949. 63p. diagrs., photos. 
(NACA RM L9C31) 



A STUDY OF SEVERAL FACTORS AFFECTING THE 
STABILITY CONTRIBUTED BY A HORIZONTAL 
TAIL AT VARIOUS VERTICAL POSITIONS ON A 
SWEPTBACK-WING AIRPLANE MODEL. Gerald V. 
Foster and Roland F. Griner. October 28, 1949. 
28p. diagrs., tab. (NACA RM L9H19) 



INVESTIGATION OF A THIN WING OF ASPECT 
RATIO 4 IN THE AMES 12-FOOT PRESSURE WIND 
TUNNEL. V - STATIC LONGITUDINAL STABILITY 
AND CONTROL THROUGHOUT THE SUBSONIC 
SPEED RANGE OF A SEMISPAN MODEL OF A 
SUPERSONIC AIRPLANE. Ben H. Johnson, Jr. , 
and Francis W. Rollins. December 8, 1949. 130p. 
diagrs., photos. (NACA RM A9I01) 



AERODYNAMIC CHARACTERISTICS AND FLYING 
QUALITIES OF A TAILLESS TRIANGULAR-WING 
AIRPLANE CONFIGURATION AS OBTAINED FROM 
FLIGHTS OF ROCKET-PROPELLED MODELS AT 
TRANSONIC AND LOW SUPERSONIC SPEEDS. 
Grady L. Mitcham, Joseph E. Stevens, and Harry P. 
Norris. February 9, 1950. 67p. diagrs., photos., 
tabs (NACA RM L9L07) 



INVESTIGATION OF DOWNWASH AND WAKE 
CHARACTERISTICS AT A MACH NUMBER OF 1.53. 
Ill - SWEPT WINGS. Edward W. Perkins and 
Thomas N. Canning. February 23, 1950. 41p. 
diagrs., tab. (NACA RM A9K02) 



THE TRANSONIC CHARACTERISTICS OF A LOW- 
ASPECT-RATIO TRIANGULAR WING WITH A 
CONSTANT-CHORD FLAP AS DETERMINED BY 
WING- FLOW TESTS, INCLUDING CORRELATION 
WITH LARGE-SCALE TESTS. George A. Rathert, 
Jr., L. Stewart Rolls, and Carl M. Hanson. 
July 18, 1950. 39p. diagrs., photo. 
(NACA RM A50E10) 



A TRANSONIC -WING INVESTIGATION IN THE 
LANGLEY 8-FOOT HIGH-SPEED TUNNEL AT HIGH 
SUBSONIC MACH NUMBERS AND AT A MACH 
NUMBER OF 1.2. WING-FUSELAGE CONFIGURA- 
TION WITH A WING OF 45° SWEEPBACK, ASPECT 
RATIO 4, TAPER RATIO 0.6, AND NACA 65A006 
AIRFOIL SECTION. Robert S. Osborne. 
October 10, 1950. 49p. diagrs., photos. 
(NACA RM L50H08) 



ELEVATOR-STABILIZER EFFECTIVENESS AND 
TRIM OF THE X-l AIRPLANE TO A MACH NUM- 
BER OF 1.06; Hubert M. Drake and John R. Carden. 
November 1, 1950. 12p. diagrs. 
(NACA RM L50G20) 



A TRANSONIC WING INVESTIGATION IN THE 
LANGLEY 8-FOOT HIGH-SPEED TUNNEL AT HIGH 
SUBSONIC MACH NUMBERS AND AT A MACH 
NUMBER OF 1.2. WING-FUSELAGE CONFIGURA- 
TION HAVING A WING OF 35° SWEEPBACK, AS- 
PECT RATIO 4, TAPER RATIO 0.6, AND NACA 
65A006 AIRFOIL SECTION. Beverly Z. Henry, Jr. 
November 15, 1950. 40p. diagrs., photo., tab. 
(NACA RM L50J09) 



THE LONGITUDINAL STABILITY, CONTROL EF- 
FECTIVENESS, AND CONTROL HINGE-MOMENT 
CHARACTERISTICS OBTAINED FROM A FLIGHT 
INVESTIGATION OF A CANARD MISSILE CONFIG- 
URATION AT TRANSONIC AND SUPERSONIC 
SPEEDS. Roy J. Niewald and Martin T. Moul. 
November 24, 1950. 43p. diagrs., photos. 
(NACA RM L50I27) 



HORIZONTAL-TAIL EFFECTIVENESS AND DOWN- 
WASH SURVEYS FOR TWO 47.7° SWEPTBACK 
WING-FUSELAGE COMBINATIONS WITH ASPECT 
RATIOS OF 5.1 AND 6.0 AT A REYNOLDS NUMBER 
OF 6.0 x 10 6 . Reino J. Salmi. January 12, 1951. 
65p. diagrs., photos., 2 tabs. (NACA RM L50K06) 



A TRANSONIC-WING INVESTIGATION IN THE 
LANGLEY 8-FOOT HIGH-SPEED TUNNEL AT HIGH 
SUBSONIC MACH NUMBERS AND AT A MACH NUM- 
BER OF 1.2. WING-FUSELAGE CONFIGURATION 
HAVING A WING OF G0° SWEEPBACK, ASPECT 
RATIO 4, TAPER RATIO 0.6, AND NACA 65A006 
AIRFOIL SECTION. Raymond B. Wood and Frank F. 
Fleming. January 24, 1951. 43p. diagrs., photo. 
(NACA RM L50J25) 



91 



(1) AERODYNAMICS 



AERODYNAMIC CHARACTERISTICS INCLUDING 
PRESSURE DISTRIBUTIONS OF A FUSELAGE AND 
THREE COMBINATIONS OF THE FUSELAGE WITH 
SWEPT- BACK WINGS AT HIGH SUBSONIC SPEEDS. 
Fred B. Sutton and Andrew Martin. February 6, 
1951. 117p. diagrs., photos., tabs. 
(NACA RM A50J26a) 



LOW -SPEED LONGITUDINAL AND WAKE AIR- 
FLOW CHARACTERISTICS AT A REYNOLDS NUM- 
BER OF 6.0 x 10 6 OF A 52° SWEPTBACK WING 
EQUIPPED WITH VARIOUS SPANS OF LEADING- 
EDGE AND TRAILING-EDGE FLAPS, A FUSELAGE, 
AND A HORIZONTAL TAIL AT VARIOUS VERTICAL 
POSITIONS. Roland F. Griner and Gerald V. Foster. 
February 28, 1951. 66p. diagrs., photo., 3 tabs. 
(NACA RM L50K29) 



INVESTIGATION OF THE EFFECTS OF GEO- 
METRIC CHANGES IN AN UNDERWING PYLON - 
SUSPENDED EXTERNAL-STORE INSTALLATION 
ON THE AERODYNAMIC CHARACTERISTICS OF A 
45° SWEPTBACK WING AT HIGH SUBSONIC 
SPEEDS. Kenneth P. Spreemann and William J. 
Alford, Jr. March 5, 1951. 91p. diagrs., photos., 
tabs. (NACA RM L50L12) 



FLIGHT INVESTIGATION OF A ROLL-STABILIZED 
MISSILE CONFIGURATION AT VARYING ANGLES 
OF ATTACK AT MACH NUMBERS BETWEEN 0.8 
AND 1.79. Jacob Zarovsky and Robert A. Gardiner. 
March 6, 1951. 38p. diagrs., photos., tab. 
(NACA RM L50H21) 



A TRANSONIC -WING INVESTIGATION IN THE 
LANGLEY 8-FOOT HIGH-SPEED TUNNEL AT 
HIGH SUBSONIC MACK NUMBERS AND AT A 
MACH NUMBER OF 1.2. WING-FUSELAGE CON- 
FIGURATION HAVING A WING OF 0° SWEEPBACK, 
ASPECT RATIO 4.0, TAPER RATIO 0.6, AND NACA 
65A0D6 AIRFOIL SECTION. Maurice S. Cahn and 
Carroll R. Bryan. March 6, 1951. 37p. diagrs., 
photos. (NACA RM L51A02) 



TESTS IN THE AMES 40- BY 80-FOOT WIND TUN- 
NEL OF AN AIRPLANE CONFIGURATION WITH AN 
ASPECT RATIO 2 TRIANGULAR WING AND AN 
ALL-MOVABLE HORIZONTAL TAIL- 
LONGITUDINAL CHARACTERISTICS. David Graham 
and David G. Koenig. April 23, 1951. 35p. diagrs., 
photo., 3 tabs. (NACA RM A51B21) 



AERODYNAMIC CHARACTERISTICS OF FOUR 
WINGS OF SWEEPBACK ANGLES 0°, 35°, 45°, AND 
60°, NACA 65AO06 AIRFOIL SECTION, ASPECT 
RATIO 4, AND TAPER RATIO 0.6 IN COMBINATION 
WITH A FUSELAGE AT HIGH SUBSONIC MACH 
NUMBERS AND AT A MACH NUMBER OF 1.2. 
Arvo A. Luoma. June 6, 1951. 59p. diagrs., photo., 
tab. (NACA RM L51D13) 



LOW -SPEED LONGITUDINAL, AND WAKE AIR- 
FLOW CHARACTERISTICS AT A REYNOLDS NUM- 
BER OF 5.5 x 10 6 OF A CIRCULAR- ARC 52° 
SWEPTBACK WING WITH A FUSELAGE AND A 
HORIZONTAL TAIL AT VARIOUS VERTICAL POSI- 
TIONS. Gerald V. Foster and Roland F. Griner. 
June 19, 1951. 44p. diagrs., tabs. 
(NACA RM L51C30) 



AN ANALYSIS OF THE EFFECTS OF AERO- 
ELASTICITY ON STATIC LONGITUDINAL STABIL- 
ITY AND CONTROL OF A SWEPT-BACK-WING 
AIRPLANE. Richard B. Skcog. August 1951. 45p. 
diagrs. (NACA RM A51C19) 



INVESTIGATION OF THE EFFECTS OF TWIST AND 
CAMBER ON THE AERODYNAMIC CHARACTER- 
ISTICS OF A 50° 38' SWEPTBACK WING OF AS- 
PECT RATIO 2.98. TRANSONIC -BUMP METHOD. 
Kenneth P. Spreemann and William J. Alford, Jr. 
August 1951. 33p. diagrs., photos., tab. 
(NACA RML51C16) 



INVESTIGATION OF THE EFFECT OF A NACELLE 
AT VARIOUS CHORDWISE AND VERTICAL POSI- 
TIONS ON THE AERODYNAMIC CHARACTERISTICS 
AT HIGH SUBSONIC SPEEDS OF A 45° SWEPTBACK 
WING WITH AND WITHOUT A FUSELAGE. 
H. Norman Silvers, Thomas J. King, Jr., and 
Thomas B. Pasteur, Jr. September 1951. 71p. 
diagrs., photos., 3 tabs. (NACA RM L51H16) 



TESTS IN THE AMES 40- BY 80-FOOT WIND TUN- 
NEL OF AN AIRPLANE CONFIGURATION WITH AN 
ASPECT RATIO 4 TRIANGULAR WING AND AN 
ALL-MOVABLE HORIZONTAL TAIL - LONGITUDI- 
NAL CHARACTERISTICS. David Graham and 
David G. Koenig. October 1951. 27p. diagrs., 
photo., 4 tabs. (NACA RM A51H10a) 



ADDITIONAL STUDIES OF THE STABILITY AND 
CONTROLLABILITY OF AN UNS WEPT -WING 
VERTICALLY RISING AIRPLANE MODEL IN 
HOVERING FLIGHT INCLUDING STUDIES OF VAR- 
IOUS TETHERED LANDING TECHNIQUES. 
William R. Bates, Powell M. Lovell, Jr., and 
Charles C. Smith, Jr. November 1951. 25p. 
diagrs., photos., tab. (NACA RM L51I07a) 



THE STATIC LONGITUDINAL CHARACTERISTICS 
AT MACH NUMBERS UP TO 0.95 OF A 
TRIANGULAR-WING CANARD MODEL HAVING A 
TRIANGULAR CONTROL. Jack D. Stephenson and 
Ralph Selan. December 1951. 72p. diagrs., photo. 
(NACA RM A51I07) 



EFFECT OF VERTICAL LOCATION OF A HORIZON- 
TAL TAIL ON THE STATIC LONGITUDINAL STA- 
BILITY CHARACTERISTICS OF A 45° SWEPTBACK- 
WING - FUSELAGE COMBINATION OF ASPECT 
RATIO 8 AT A REYNOLDS NUMBER OF 4.0 x 10 6 . 
Relno J. Salmi and William A. Jacques. January 
1952. 42p. diagrs., photos. (NACA RM L51J08) 



TESTS IN THE AMES 40- BY 80-FOOT WIND TUN- 
NEL OF AN AIRPLANE CONFIGURATION WITH AN 
ASPECT RATIO 2 TRIANGULAR WING AND AN 
ALL-MOVABLE HORIZONTAL TAIL - LATERAL 
CHARACTERISTICS. David Graham and David G. 
Koenig. February 1952. 38p. diagrs., 2 tabs. 
(NACA RM A51L03) 



92 



(1) AERODYNAMICS 



WIND-TUNNEL INVESTIGATION AT LOW SPEED OF 
A TWISTED AND CAMBERED WING SWEPT BACK 
63° WITH VORTEX GENERATORS AND FENCES. 
James A. Weiberg and George B. McCullough. 
March 1952. 45p. diagrs., photos., 3 tabs. 
(NACA RM A52A17) 



WIND-TUNNEL INVESTIGATION OF THE AERODY- 
NAMIC CHARACTERISTICS IN PITCH OF WING- 
FUSELAGE COMBINATIONS AT HIGH SUBSONIC 
SPEEDS. ASPECT-RATIO SERIES. Richard E. 
Kuhn and James W. Wiggins. April 1952. 42p. 
diagrs., photos., tab. (NACA RM L52A29) 



AN INVESTIGATION THROUGHOUT THE SUBSONIC 
SPEED RANGE OF A FULL-SPAN AND A SEMI- 
SPAN MODEL OF A PLANE WING AND OF A 
CAMBERED AND TWISTED WING, ALL HAVING 
45° OF SWEEPBACK. Harry H. Shibata, Angelo 
Bandettini, and Joseph Cleary. June 1952. 85p. 
diagrs., photos. (NACA RM A52D01) 



LONGITUDINAL STABILITY AND CONTROL CHAR- 
ACTERISTICS FROM A FLIGHT INVESTIGATION 
OF A CRUCIFORM CANARD MISSILE CONFIGURA- 
TION HAVING AN EXPOSED WING-CANARD AREA 
RATIO OF 16:1. Martin T. Moul and Andrew R. 
Wineman. June 1952. 32p. diagrs., photos. 
(NACARML52D24a) 



WIND-TUNNEL INVESTIGATION OF THE AERO- 
DYNAMIC CHARACTERISTICS IN PITCH OF WING- 
FUSELAGE COMBINATIONS AT HIGH -SUBSONIC 
SPEEDS. SWEEP SERIES. James W. Wiggins and 
Richard E. Kuhn. July 1952. 41p. diagrs., photos. 
(NACA RM L52D18) 



EFFECT OF CAMBER AND TWIST ON THE STA- 
BILITY CHARACTERISTICS OF MODELS HAVING A 
45° SWEPT WING AS DETERMINED BY THE FREE- 
FALL METHOD AT TRANSONIC SPEEDS. Maurice 
D. White. August 1952. 35p. diagrs., photos., tab. 
(NACA RMA52F16) 



LONGITUDINAL STABILITY, TRIM, AND DRAG 
CHARACTERISTICS OF A ROCKET-PROPELLED 
MODEL OF AN AIRPLANE CONFIGURATION HAV- 
ING A 45° SWEPTBACK WING AND AN UNSWEPT 
HORIZONTAL TAIL. James H. Parks and Alan B. 
Kehlet. August 1952. 29p. diagrs., photos., tab. 
(NACA RM L52F05) 



LONGITUDINAL STABILITY AND CONTROL CHAR- 
ACTERISTICS OF A CANARD MISSILE CONFIGURA- 
TION FOR MACH NUMBERS FROM 1.1 TO 1.93 AS 
DETERMINED FROM FREE-FLIGHT AND WIND- 
TUNNEL INVESTIGATIONS. Howard J. Curfman, 
Jr., and Carl E. Grigsby. August 1952. 28p. 
diagrs.. tab. (NACA RM L52F06) 



PRELIMINARY RESULTS OF HORIZONTAL-TAIL 
LOAD MEASUREMENTS OF THE BELL X-5 RE- 
SEARCH AIRPLANE. John T. Rogers and Angel H. 
Dunn. August 15, 1952. 22p. diagrs., photos., 
tabs. (NACA RM L52G14) 



THE USE OF LEADING-EDGE AREA SUCTION TO 
INCREASE THE MAXIMUM LIFT COEFFICIENT OF 
A 35° SWEPT-BACK WING. Curt A. Holzhauserand 
Robert K. Martin. September 1952. 37p. diagrs., 
photo., 3 tabs. (NACA RM A52G17) 

A CORRELATION WITH FLIGHT TESTS OF RE- 
SULTS OBTAINED FROM THE MEASUREMENT OF 
WING PRESSURE DISTRIBUTIONS ON A 1/4-SCALE 
MODEL OF THE X-l AIRPLANE (10-PERCENT- 
THICK WING). Jack F. Runckel and James H. 
Henderson. September 1952. 60p. diagrs., photos., 
tab. (NACA RM L52E29) 



INVESTIGATION OF THE LOW-SPEED AERO- 
DYNAMIC CHARACTERISTICS OF A VARIABLE - 
SWEEP AIRPLANE MODEL WITH A WING HAVING 
PARTIAL-SPAN CAMBERED- LEADING-EDGE 
MODIFICATIONS. Robert E. Becht and Andrew L. 
Byrnes. Jr. September 1952. 47p. diagrs., photos. 
(NACA RM L52G08a) 



THE EFFECTS OF SWEEPBACK ON LONGITUDINAL 
CHARACTERISTICS OF A 1/30-SCALE SEMISPAN 
MODEL OF THE BELL X-5 AIRPLANE AS DETER- 
MINED FROM NACA WING-FLOW TESTS AT 
TRANSONIC SPEEDS. Joseph J. Kolnick and 
Robert M. Kennedy. November 1952. 48p. diagrs., 
photos., tab. (NACA RM L52I23) 



THE LONGITUDINAL CHARACTERISTICS AT MACH 
NUMBERS UP TO 0.9 OF A WING-FUSELAGE-TAIL 
COMBINATION HAVING A WING WITH 40° OF 
SWEEPBACK AND AN ASPECT RATIO OF 10. 
Bruce E. Tinling. December 1952. 41p. diagrs., 
photo., tab. (NACA RM A52I19) 



EFFECTS OF TWIST AND CAMBER, FENCES, AND 
HORIZONTAL-TAIL HEIGHT ON THE LOW-SPEED 
LONGITUDINAL STABILITY CHARACTERISTICS OF 
A WING- FUSELAGE COMBINATION WITH A 45° 
SWEPTBACK WING OF ASPECT RATIO 8 AT A 
REYNOLDS NUMBER OF 4.0 x 106. Gerald V. 
Foster. December 1952. 30p. diagrs., photo. 
(NACA RM L52J03) 



LONGITUDINAL-CONTROL EFFECTIVENESS AND 
DOWNWASH CHARACTERISTICS AT TRANSONIC 
SPEEDS OF A 1/30-SCALE SEMISPAN MODEL OF 
THE BELL X-5 AIRPLANE AS DETERMINED BY 
THE NACA WING-FLOW METHOD. Norman S. 
Silsby and Garland J. Morris. January 1953. 48p. 
diagrs.. photos., 2 tabs. (NACA RM L52K12) 



INVESTIGATION OF THE EFFECT OF CHORDWISE 
POSITIONING AND SHAPE OF AN UNDERWING NA- 
CELLE ON THE HIGH-SPEED AERODYNAMIC 
CHARACTERISTICS OF A 45° SWEPTBACK 
TAPERED-IN-THICKNESS-RATIO WING OF AS- 
PECT RATIO 6. H. Norman Silvers and Thomas J. 
King, Jr. January 1953. 50p. diagrs. 
(NACA RM L52K25) 



TESTS IN THE AMES 40- BY 80-FOOT WIND TUN- 
NEL OF AN AIRPLANE MODEL WITH AN ASPECT 
RATIO 4 TRIANGULAR WING AND AN ALL- 
MOVABLE HORIZONTAL TAIL - HIGH -LIFT DE- 
VICES AND LATERAL CONTROLS. Ralph W. 
Franks. February 1953. 45p. diagrs., photo., 2 
tabs. (NACA RM A52K13) 



93 



(1) AERODYNAMICS 



TESTS IN THE AMES 40- BY 80-FOOT WIND TUN- 
NEL OF TWO AIRPLANE MODELS HAVING AS- 
PECT RATIO 2 TRAPEZOIDAL WINGS OF TAPER 
RATIOS 0.33 AND 0.20. Ralph W. Franks. 
February 1953. 56p. diagrs., photos., 3 tabs. 
(NACARMA52L16) 



A FLIGHT INVESTIGATION OF THE EFFECT OF 
LEADING-EDGE CAMBER ON THE AERODYNAMIC 
CHARACTERISTICS OF A SWEPT -WING AIRPLANE. 
Seth B. Anderson, Frederick H. Matteson, and 
Rudolph D. Van Dyke, Jr. February 1953. 23p. 
diagrs., photos., tab. (NACA RM A52L16a) 



PRELIMINARY RESULTS OF STABILITY AND CON- 
TROL INVESTIGATION OF THE BELL X-5 RE- 
SEARCH AIRPLANE. Thomas W. Finch and Donald 
W. Briggs. February 1953. 35p. diagrs., photos., 
tabs. (NACA RM L52K18b) 



THE EFFECTS OF FUSELAGE SIZE ON THE LOW- 
SPEED LONGITUDINAL AERODYNAMIC CHARAC- 
TERISTICS OF A THIN 60° DELTA WING WITH 
AND WITHOUT A DOUBLE SLOTTED FLAP. John 
M. Riebe. February 1953. 24p. diagrs., photo., 
tab. {NACA RM L52L29a) 



FLIGHT DETERMINATION OF THE STATIC LONGI- 
TUDINAL STABILITY BOUNDARIES OF THE*BELL 
X-5 RESEARCH AIRPLANE WITH 59° SWEEPBACK. 
Thomas W. Finch and Joseph A. Walker. February 
1953. 51p. diagrs., photo., tab. 
(NACA RM L53A09b) 



LOW-SPEED LONGITUDINAL CHARACTERISTICS 

OF AN UNSWEPT HEXAGONAL WING WITH AND 
WITHOUT A FUSELAGE AND A HORIZONTAL TAIL 
LOCATED AT VARIOUS POSITIONS AT REYNOLDS 
NUMBERS FROM 2.8 x 10 6 TO 7.6 x 10 6 . Gerald V. 
Foster. Ernst F. Mollenberg, and Robert L. Woods. 
February 26, 1953. 63p. diagrs., photos., 3 tabs. 
(NACA RM L52Lllb) 



TESTS IN THE AMES 40- BY 80-FOOT WIND TUN- 
NEL OF AN AIRPLANE CONFIGURATION WITH AN 
ASPECT RATIO 3 TRIANGULAR WING AND AN 
ALL-MOVABLE HORIZONTAL TAIL - LONGITU- 
DINAL AND LATERAL CHARACTERISTICS. David 
G. Koenig. April 1953. 61p. diagrs., photos., 
4 tabs. (NACA RM A52L15) 



INVESTIGATION OF THE EFFECTS OF WING AND 
TAIL MODIFICATIONS ON THE LOW-SPEED STA- 
BILITY CHARACTERISTICS OF A MODEL HAVING 
A THIN 40° SWEPT WING OF ASPECT RATIO 3.5. 
Joseph Weil, William C. Sleeman, Jr., and Andrew 
L. Byrnes, Jr. April 1953. 95p. diagrs., photos., 
tab. (NACA RM L53C09) 



WIND-TUNNEL INVESTIGATION AT HIGH SUB- 
SONIC SPEEDS OF A SPOILER-SLOT-DEFLECTOR 
COMBINATION ON AN NACA 65A006 WING WITH 
QUARTER-CHORD LINE SWEPT BACK 32.6°. 
Raymond D. Vogler. May 1953. 24p. diagrs. 
(NACA RM L53D17) 



THE EFFECTS OF NACELLES AND OF EXTENDED 
SPLIT FLAPS ON THE LONGITUDINAL CHARAC- 
TERISTICS OF A WING- FUSELAGE -TAIL COMBI- 
NATION HAVING A WING WITH 40° OF SWEEP- 
BACK AND AN ASPECT RATIO OF 10. Bruce E. 
Tinling and Armando E. Lopez. June 1953. 47p. 
diagrs., tab. (NACA RM A53D06) 

TESTS IN THE AMES 40- BY 80 -FOOT WIND TUN- 
NEL OF AN AIRPLANE CONFIGURATION WITH A 
VARIABLE -INCIDENCE TRIANGULAR WING AND 
AN ALL-MOVABLE HORIZONTAL TAIL. David G. 
Koenig. June 1953. 42p. diagrs., photo., tabs. 
(NACA RM A53D21) 



INVESTIGATION AT LOW SPEED OF THE FLOW 
FIELD BEHIND THE LIFTING SURFACES OF A 
MODEL EQUIPPED WITH A 60° TRIANGULAR WING 
AND A 60° TRIANGULAR CANARD TAIL. Ernest E. 
Newman and Jones F. Cahill. June 1953. 44p. 
diagrs., photos., tab. (NACA RM L53C30) 



LONGITUDINAL STABILITY AND WAKE -FLOW 
CHARACTERISTICS OF A TWISTED AND 
CAMBERED WING-FUSELAGE COMBINATION OF 
45° SWEEPBACK AND ASPECT RATIO 8 WITH A 
HORIZONTAL TAIL AND STALL -CONTROL DE- 
VICES AT A REYNOLDS NUMBER OF 4.0 x 10 6 . 
Gerald V. Foster. June 1953. 51p. diagrs., 
photos., tab. (NACA RM L53D08) 



EFFECTS OF HORIZONTAL-TAIL HEIGHT AND A 
WING LEADING-EDGE MODIFICATION CON- 
SISTING OF A FULL-SPAN FLAP AND A PARTIAL- 
SPAN CHORD-EXTENSION ON THE AERODYNAMIC 
CHARACTERISTICS IN PITCH AT HIGH SUBSONIC 
SPEEDS OF A MODEL WITH A 45° SWEPTBACK 
WING. William D. Morrison, Jr and William J 
Alford, Jr. June 1953. 37p. diagrs., photo., tab. 
(NACA RM L53E06) 



WIND-TUNNEL INVESTIGATION OF THE AERODY- 
NAMIC CHARACTERISTICS IN PITCH OF WING- 
FUSELAGE COMBINATIONS AT HIGH SUBSONIC 
SPEEDS. TAPER- RATIO SERIES. Thomas J. 
Kin^. Jr. and Thomas B. Pasteur, Jr. June 1953. 
37p. diagrs., photos., tab. (NACA RM L53E20) 



WIND-TUNNEL INVESTIGATION OF THE EFFECTS 
OF GEOMETRIC DIHEDRAL ON THE AERODYNAM- 
IC CHARACTERISTICS IN PITCH AND SIDESLIP OF 
AN UNSWEPT- AND A 45° SWEPTBACK-WING- 
FUSELAGE COMBINATION AT HIGH SUBSONIC 
SPEEDS. Richard E. Kuhn and John W. Draper. 
July 1953. 41p. diagrs., photos. 
(NACA RM L53F09) 



THE EFFECTS OF LEADING-EDGE EXTENSIONS, 
A TRAILING-EDGE EXTENSION, AND A FENCE 
ON THE STATIC LONGITUDINAL STABILITY OF A 
WING-FUSELAGE-TAIL COMBINATION HAVING 
A WING WITH 350 F SWEEPBACK AND AN AS- 
PECT RATIO OF 4.5. Ralph Selan and Angelo 
Bandettini. August 1953. 8lp. diagrs., photos., 
tabs. (NACA RM A53E12) 



THE EFFECTS OF FENCES ON THE HIGH-SPEED 
LONGITUDINAL STABILITY OF A SWEPT -WING 
AIRPLANE. Richard S. Bray. August 1953. 37p. 
diagrs., photos., tabs. (NACA RM A53F23) 



94 



(1) AERODYNAMICS 



LONGITUDINAL FLIGHT CHARACTERISTICS OF 
THE BELL X-5 RESEARCH AIRPLANE AT 59° 
SWEEPBACK WITH MODIFIED WING ROOTS. 

James A. Martin. August 1953. 25p. diagrs., 
photos., tab. (NACA RM L53E28) 

EFFECT OF REDUCTION IN THICKNESS FROM 6 
TO 2 PERCENT AND REMOVAL OF THE POINTED 
TIPS ON THE SUBSONIC STATIC LONGITUDINAL 
STABILITY CHARACTERISTICS OF A 60° TRIANGU- 
LAR WING IN COMBINATION WITH A FUSELAGE. 
William E. Palmer. August 1953. 44p. diagrs., 
photo., tab. (NACA RM L53F24) 

A TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE LONGITUDINAL STABILITY AND CONTROL 
CHARACTERISTICS OF A 0.09-SCALE MODEL OF 
THE BELL X-5 RESEARCH AIRPLANE AND COM- 
PARISON WITH FLIGHT. Ralph P. Bielat and 
George S. Campbell. October 1953. 65p. diagrs., 
photo. (NACA RM L53H18) 

FREE-FLIGHT-TUNNEL INVESTIGATION OF THE 
LOW-SPEED STABILITY AND CONTROL CHARAC- 
TERISTICS OF A CANARD AIRPLANE MODEL. 
Joseph L. Johnson, Jr., and John W. Paulson. 
October 1953. 37p. diagrs., photo., 2 tabs. (NACA 
RM L53I11) 

WIND-TUNNEL INVESTIGATION AT LOW SPEED 
OF THE EFFECT OF VARYING THE RATIO OF 
BODY DIAMETER TO WING SPAN FROM 0.1 TO 0.8 
ON THE AERODYNAMIC CHARACTERISTICS IN 
PITCH OF A 45° SWEPTBACK-WING— BODY 
COMBINATION. Harold S. Johnson. November 
1953 32p. diagrs.. photo., tab. 
(NACA RM L53J09a) 

DOWNWASH BEHIND A TRIANGULAR WING OF 
ASPECT RATIO 3 - TRANSONIC BUMP METHOD. 
John A. Axelson. December 1953. 37p. diagrs., 
photo., tab. (NACA RM A53I23) 

THE RESULTS OF WIND-TUNNEL TESTS AT LOW 
SPEEDS OF A FOUR-ENGINE PROPELLER -DRIVEN 
AIRPLANE CONFIGURATION HAVING A WING WITH 
40° OF SWEEPBACK AND AN ASPECT RATIO OF 
10. George G. Edwards, Donald A. Buell, and 
Jerald K. Dickson. December 1953. 121p. diagrs., 
photo., tabs. (NACA RM A53I28) 



AN EXPERIMENTAL AND THEORETICAL INVES- 
TIGATION AT HIGH SUBSONIC SPEEDS OF THE 
EFFECTS OF HORIZONTAL-TAIL HEIGHT ON THE 
AERODYNAMIC CHARACTERISTICS IN SIDESLIP 
OF AN UNSWEPT, UNTAPERED TAIL ASSEMBLY. 
Harleth G. Wiley and Donald R. Riley. December 
1953. 71p. diagrs., tab. (NACA RM L53J19) 

WIND-TUNNEL INVESTIGATION AT HIGH AND LOW 
SUBSONIC MACH NUMBERS OF TWO UNSWEPT 
WINGS HAVING NACA 2-006 AND NACA 65A006 
AIRFOIL SECTIONS. Stanley F. Racisz. 
December 1953. 40p. diagrs., photo., tab. 
(NACA RM L53J29) 

WIND-TUNNEL INVESTIGATION AT LOW SPEED 
OF THE EFFECTS OF CHORDWISE WING FENCES 
AND HORIZONTAL-TAIL POSITION ON THE 
STATIC LONGITUDINAL STABILITY CHARACTER- 
ISTICS OF AN AIRPLANE MODEL WITH A 35° 
SWEPTBACK WING. M. J. Queljo, Byron M. 
Jaquet, and Walter D. Wolhart. 1954. 11, 29p. 
diagrs., photos., tab. (NACA Rept. 1203. Super- 
sedes RM L50K07; RM L51H17) 



THE EFFECTS OF OPERATING PROPELLERS ON 
THE LONGITUDINAL CHARACTERISTICS AT HIGH 
SUBSONIC SPEEDS OF A FOUR-ENGINE TRACTOR 
AIRPLANE CONFIGURATION HAVING A WING 
WITH 40° OF SWEEPBACK AND AN ASPECT RATIO 
OF 10. Fred B. Sutton and Fred A. Demele. 
January 1954. 106p. diagrs., photo., 11 tabs. 
(NACA RM A53J23) 

STABILITY CHARACTERISTICS AT LOW SPEED OF 
A VARIABLE -SWEEP AIRPLANE MODEL HAVING 
A PARTIALLY CAMBERED WING WITH SEVERAL 
CHORD-EXTENSION CONFIGURATIONS. Robert E. 
Becht. February 1954. 37p. diagrs., photos. 
(NACA RM L53L14) 



THE EFFECTS OF HORIZONTAL-TAIL HEIGHT 
AND A PARTIAL-SPAN LEADING-EDGE EXTEN- 
SION ON THE STATIC LONGITUDINAL STABILITY 
OF A WING- FUSELAGE -TAIL COMBINATION 
HAVING A SWEPTBACK WING. Angelo Bandettini 
and Ralph Selan. March 1954. 54p. diagrs.. 
photos., 2 tabs. (NACA RM A53J07) 



PRELIMINARY INVESTIGATION AT SUBSONIC AND 
TRANSONIC SPEEDS OF THE AERODYNAMIC 
CHARACTERISTICS OF A BIPLANE COMPOSED OF 
A SWEPTBACK AND A SWEPTFORWARD WING 
JOINED AT THE TIPS. Jones F. Cahill and 
Dexter H. Stead. March 1954. 19p. diagrs., 
photos. (NACA RM L53L24b) 

DISTRIBUTION OF LIFT AND PITCHING MOMENT 
BETWEEN WING AND FUSELAGE AND EFFECTS 
OF WING FLEXIBILITY AND DIVE BRAKE ON A 
1/30-SCALE SEMISPAN MODEL OF THE BELL X-5 
AIRPLANE AT TRANSONIC SPEEDS AS DETER- 
MINED BY THE NACA WING-FLOW METHOD. 
Garland J. Morris and Norman S, Silsby. March 
1954. 46p. diagrs., photos., tab. 
(NACA RM L54A11) 

FLIGHT INVESTIGATION OF THE EFFECTS OF A 
PARTIAL-SPAN LEADING-EDGE CHORD EXTEN- 
SION OF THE AERODYNAMIC CHARACTERISTICS 
OF A 35° SWEPT -WING FIGHTER AIRPLANE. 
Frederick H. Matteson and Rudolph D. Van Dyke, Jr. 
April 1954. 34p. diagrs., photos., tabs. 
(NACA RM A54B26) 

EFFECTS OF SWEEP AND THICKNESS ON THE 
STATIC LONGITUDINAL AERODYNAMIC CHARAC- 
TERISTICS OF A SERIES OF THIN, LOW-ASPECT- 
RATIO HIGHLY TAPERED WINGS AT TRANSONIC 
SPEEDS. TRANSONIC-BUMP METHOD. Albert G. 
Few Jr., and Paul G. Fournier. April 1954. 107p. 
diagrs., photo., tab. (NACA RM L54B25) 



THE EFFECT OF BLUNT-TRAILTNG-EDGE MODI- 
FICATIONS ON THE HIGH-SPEED STABILITY AND 
CONTROL CHARACTERISTICS OF A SWEPT-WING 
FIGHTER AIRPLANE. Melvin Sadoff, Frederick H. 
Matteson, and Rudolph D. Van Dyke, Jr. May 1954. 
55p. diagrs., photos., tab. (NACA RM A54C31) 



EFFECT AT TRANSONIC SPEEDS OF INBOARD 
SPOILERS ON THE STATIC LONGITUDINAL STA- 
BILITY CHARACTERISTICS OF A 45° SWEPTBACK 
WING-BODY COMBINATION HAVING A LEADING- 
EDGE CHORD-EXTENSION. James H. Henderson. 
June 1954. 24p. diagrs., photo. 
(NACA RM L54D13) 



95 



(1) AERODYNAMICS 



LONGITUDINAL STABILITY AND DRAG CHAR- 
ACTERISTICS OF A FIN-STABILIZED BODY OF 
REVOLUTION WITH A FINENESS RATIO OF 12 AS 
MEASURED BY THE FREE-FALL METHOD, 
Max C. Kurbjun. June 1954. 19p. diagrs., photos., 
tab. (NACA RM L54E13) 



EFFECTS OF HIGH-LIFT DEVICES AND 
HORIZONTAL-TAIL LOCATION ON THE LOW- 
SPEED CHARACTERISTICS OF A LARGE-SCALE 
45° SWEPT-WING AIRPLANE CONFIGURATION. 
Ralph L. Maki and Ursel R. Embry. August 1954. 
46p. diagrs., photo. , tabs. (NACA RM A54E10) 



STATIC LONGITUDINAL STABILITY CHARACTER- 
ISTICS OF A COMPOSITE-PLAN-FORM WING 
MODEL INCLUDING SOME COMPARISONS WITH A 
45° SWEPTBACK WING AT TRANSONIC SPEEDS. 
Walter D. Wolhart. August 1954. 36p. diagrs., 
photo., tabs. (NACA RM L54F24) 



ANALYSIS OF WIND-TUNNEL TESTS AT LOW 
SPEEDS OF A FOUR-ENGINE PROPELLER- 
DRIVEN AIRPLANE CONFIGURATION HAVING A 
WING WITH 40° OF SWEEPBACK. George G. 
Edwards and Donald A. Buell. October 1954. 137p. 
diagrs., photos., 2 tabs. (NACA RM A54F14) 



EFFECTS OF WING POSITION AND FUSELAGE 
SIZE ON THE LOW-SPEED STATIC AND ROLLING 
STABILITY CHARACTERISTICS OF A DELTA-WING 
MODEL. Alex Goodman and David F. Thomas, Jr. 
1955. ii, 31p. diagrs., photos., tabs. 
(NACA Rept. 1224. Supersedes TN 3063) 



A METHOD FOR THE DESIGN OF SWEPTBACK 
WINGS WARPED TO PRODUCE SPECIFIED FLIGHT 
CHARACTERISTICS AT SUPERSONIC SPEEDS. 
Warren A Tucker. 1955. i, 17p. diagrs., tabs. 
(NACA Rept. 1226. Supersedes RM L51 F08) 



A FLIGHT EVALUATION OF THE LONGITUDINAL 
STABILITY CHARACTERISTICS ASSOCIATED WITH 
THE PITCH-UP OF A SWEPT-WING AIRPLANE IN 
MANEUVERING FLIGHT AT TRANSONIC SPEEDS. 
Seth B. Anderson and Richard S. Bray. 1955. 11, 
12p. diagrs., photo., tab. (NACA Rept, 1237. 
Supersedes RM A51I12) 



THE DYNAMIC-RESPONSE CHARACTERISTICS OF 
A 350 SWEPT-WING AIRPLANE AS DETERMINED 
FROM FLIGHT MEASUREMENTS. William C. 
Triplett, Stuart C. Brown, and G. Allan Smith. 
1955. ii, 25p. diagrs., tabs. (NACA Rept. 1250. 
Supersedes RM A51G27; RM A52I17) 



FLIGHT DETERMINATION OF THE LONGITUDINAL 
STABILITY AND CONTROL CHARACTERISTICS OF 
THE BELL X-5 RESEARCH AIRPLANE AT 58.7° 
SWEEPBACK. Thomas W. Finch. May 1955. 30p. 
diagrs., photo., tab. (NACA RM H55C07) 



EFFECTS OF SWEEP ON THE MAXIMUM-LIFT 
CHARACTERISTICS OF FOUR ASPECT-RATIO-4 
WINGS AT TRANSONIC SPEEDS. Thomas R. Turner. 
July 1955, 25p. diagrs. (NACA TN 3468. Formerly 
RM L50H11) 



WIND-TUNNEL INVESTIGATION AT LOW SPEED 
OF EFFECT OF SIZE AND POSITION OF CLOSED 
AIR DUCTS ON STATIC LONGITUDINAL AND 
STATIC LATERAL STABILITY CHARACTERISTICS 
OF UNSWEPT-MIDWING MODELS HAVING WINGS 
OF ASPECT RATIO 2, 4, AND 6. Byron M. Jaquet 
and James L. Williams. September 1955. 45p. 
diagrs., photos., tabs. (NACA TN 3481) 

THE EFFECTIVENESS OF WING VORTEX GENERA- 
TORS IN IMPROVING THE MANEUVERING CHARAC- 
TERISTICS OF A SWEPT-WING AIRPLANE AT 
TRANSONIC SPEEDS. Norman M. McFadden, 
George A. Rathert, Jr. , and Richard S. Bray. 
September 1955. 43p. diagrs. , photos. , tab. 
(NACA TN 3523. Supersedes RM A51J18) 



FLIGHT MEASUREMENTS OF THE DYNAMIC 
LATERAL AND LONGITUDINAL STABILITY OF 
THE BELL X-5 RESEARCH AIRPLANE AT 58.7° 
SWEEPBACK. Edward N. Videan. October 1955. 
68p. diagrs., photo., tabs. (NACA RM H55H10) 



AERODYNAMIC CHARACTERISTICS OF A SMALL- 
SCALE SHROUDED PROPELLER AT ANGLES OF 
ATTACK FROM 0° TO 90°. Lysle P. Parlett. 
November 1955. 12p. diagrs. (NACA TN 3547) 



EXPERIMENTAL INVESTIGATION AT LOW SPEED 
OF EFFECTS OF FUSELAGE CROSS SECTION ON 
STATIC LONGITUDINAL AND LATERAL STABILITY 
CHARACTERISTICS OF MODELS HAVING 0° AND 
45° SWEPTBACK SURFACES. William Letko and 
James L. Williams. December 1955. 45p. diagrs., 
tabs. (NACA TN 3551) 



A SECOND-ORDER SHOCK-EXPANSION METHOD 
APPLICABLE TO BODIES OF REVOLUTION NEAR 
ZERO LIFT. Clarence A. Syvertson and David H. 
Dennis. January 1956. 57p. diagrs., tabs. 
(NACA TN 3527) 



INVESTIGATION OF THE EFFECTS OF GROUND 
PROXIMITY AND PROPELLER POSITION ON THE 
EFFECTIVENESS OF A WING WITH LARGE-CHORD 
SLOTTED FLAPS IN REDIRECTING PROPELLER 
SLIPSTREAMS DOWNWARD FOR VERTICAL TAKE- 
OFF. Richard E. Kuhn. March 1956. 38p. 
diagrs., photos., tab. (NACA TN 3629) 



SOME EFFECTS OF FUSELAGE FLEXIBILITY ON 
LONGITUDINAL STABILITY AND CONTROL. 
Bernard B. Klawans and Harold I. Johnson. April 
1956. 42p. diagrs., tab. (NACA TN 3543) 



AN ANALYSIS OF ESTIMATED AND EXPERI- 
MENTAL TRANSONIC DOWNWASH CHARACTER- 
ISTICS AS AFFECTED BY PLAN FORM AND THICK- 
NESS FOR WING AND WING- FUSELAGE CONFIG- 
URATIONS. Joseph Weil, George S. Campbell and 
Margaret S. Dlederlch. April 1956. 92p. diagrs., 
photos., tabs. (NACA TN 3628. Supersedes 
RM L52I22) 



A WIND-TUNNEL INVESTIGATION OF A 0.4-SCALE 
MODEL OF AN ASSAULT-TRANSPORT AIRPLANE 
WITH BOUNDARY-LAYER CONTROL APPLIED. 
Marvin P. Fink, Bennie W. Cocke, and Stanley 
Lipson. May 1956. 63p. diagrs., photos. 
(NACA RM L55G26a) 



96 



(1) AERODYNAMICS 



STATIC LONGITUDINAL AND LATERAL STABILITY 
CHARACTERISTICS AT LOW SPEED OF UNSWEPT- 
MIDWING MODELS HAVING WINGS WITH AN 
ASPECT RATIO OF 2, 4, OR 6. Walter D. Wolhart 
and David F. Thomas, Jr. May 1956. 41p. 
diagrs., photos., tabs. (NACA TN 3649) 

INVESTIGATION AT ZERO FORWARD SPEED OF A 
LEADING-EDGE SLAT AS A LONGITUDINAL CON- 
TROL DEVICE FOR VERTICALLY RISING AIR- 
PLANES THAT UTILIZE THE REDIRECTED- 
SLIPSTREAM PRINCIPLE. Richard E. Kuhn. 
May 1956. 33p. diagrs., photos. (NACA TN 3692} 

PRELIMINARY INVESTIGATION OF THE EFFEC- 
TIVENESS OF A SLIDING FLAP IN DEFLECTING A 
PROPELLER SLIPSTREAM DOWNWARD FOR 
VERTICAL TAKE-OFF. Richard E. Kuhn and 
Kenneth P. Spreemann. May 1956. 25p. diagrs., 
photo. (NACA TN 3693) 



WIND-TUNNEL INVESTIGATION OF THE EFFECT 
OF CLIPPING THE TIPS OF TRIANGULAR WINGS 
OF DIFFERENT THICKNESS, CAMBER, AND AS- 
PECT RATIO - TRANSONIC BUMP METHOD. 
Horace F. Emerson. June 1956. 183p. diagrs., 
photo., tabs. (NACA TN 3671. Supersedes 
RM A53L03) 



INVESTIGATION OF LATERAL CONTROL NEAR 
THE STALL. FLIGHT TESTS WITH HIGH-WING 
AND LOW-WING MONOPLANES OF VARIOUS CON- 
FIGURATIONS. Fred E. Weick and H. Norman 
Abramson, Agricultural and Mechanical College of 
Texas. June 1956. 34p. diagrs., photos., tabs. 
(NACA TN 3676) 



INVESTIGATION OF LATERAL CONTROL NEAR 
THE STALL. ANALYSIS FOR REQUIRED LONGI- 
TUDINAL TRIM CHARACTERISTICS AND DISCUS- 
SION OF DESIGN VARIABLES. Fred E. Weick and 
H. Norman Abramson, Agricultural and Mechanical 
College of Texas. June 1956. 91p. diagrs., tabs. 
(NACA TN 3677) 



AN INVESTIGATION OF FORWARD-LOCATED 
FDCED SPOILERS AND DEFLECTORS AS GUST 
ALLEVIATORS ON AN UNSWEPT-WING MODEL. 
Delwin R. Croom, C. C. Shuiflebarger, and 
Jarrett K. Huffman. June 1956. 26p. diagrs., 
photo. (NACA TN 3705) 



(1.8. 1. 1. 2) 

Lateral 

LOW-SPEED WIND-TUNNEL TESTS OF A PILOT - 
LESS AIRCRAFT HAVING HORIZONTAL AND 
VERTICAL WINGS AND CRUCIFORM TAIL. 
N. Mastrocola and A. Assadourian. August 19, 
1947. lOOp. diagrs., photos., tab. 
(NACA RM L6J18a) 

AERODYNAMIC STUDY OF A WING-FUSELAGE 
COMBINATION EMPLOYING A WING SWEPT BACK 
63° - AERODYNAMIC CHARACTERISTICS IN 
SIDESLIP OF A LARGE-SCALE MODEL HAVING A 
63° SWEPT-BACK VERTICAL TAIL. Gerald M. 
McCormack. October 7, 1949. 26p. diagrs., 
photos. (NACA RM A9F14) 



WING-DROPPING CHARACTERISTICS OF SOME 
STRAIGHT AND SWEPT WINGS AT TRANSONIC 
SPEEDS AS DETERMINED WITH ROCKET- 
POWERED MODELS. David G. Stpne. May 26, 
1950. 12p. dlagTs., tab. (NACA RM L50C01) 



NOTES ON LOW-LIFT BUFFETING AND WING 
DROPPING AT MACH NUMBERS NEAR 1. Paul E. 
Purser. March 16, 1951. 22p. diagrs., tab. 
(NACA RM L51A30) 



TESTS IN THE AMES 40- BY 80-FOOT WIND TUN- 
NEL OF AN AIRPLANE CONFIGURATION WITH AN 
ASPECT RATIO 2 TRIANGULAR WING AND AN 
ALL-MOVABLE HORIZONTAL TAIL - LATERAL 
CHARACTERISTICS. David Graham and David G. 
Koenig. February 1952. 38p, diagrs., 2 tabs. 
(NACA RM A51L03) 



AN APPROXIMATION TO THE EFFECT OF GEO- 
METRIC DIHEDRAL ON THE ROLLING MOMENT 
DUE TO SIDESLIP FOR WINGS AT TRANSONIC AND 
SUPERSONIC SPEEDS. Paul E. Purser. April 
1952. lOp. diagrs. (NACA RM L52B01) 



INVESTIGATION OF THE LOW-SPEED AERO- 
DYNAMIC CHARACTERISTICS OF A VARIABLE - 
SWEEP AIRPLANE MODEL WITH A WING HAVING 
PARTIAL-SPAN CAMBERED- LEADING-EDGE 
MODIFICATIONS. Robert E. Becht and Andrew L. 
Byrnes, Jr. September 1952. 47p. diagrs., photos. 
(NACA RM L52G08a) 



TESTS IN THE AMES 40- BY 80-FOOT WIND TUJN- 
NEL OF AN AIRPLANE MODEL WITH AN ASPECT 
RATIO 4 TRIANGULAR WING AND AN ALL- 
MOVABLE HORIZONTAL TAIL - HIGH-LIFT DE- 
VICES AND LATERAL CONTROLS. Ralph W. 
Franks. February 1953. 45p. diagrs., photo., 2 
tabs. (NACA RM A52K13) 



FLIGHT MEASUREMENTS OF THE STABILITY 
CHARACTERISTICS OF THE BELL X-5 RESEARCH 
AIRPLANE IN SIDESLIPS AT 59° SWEEPBACK. 
Joan M. Childs. February 1953. 23p. diagrs., 
photos., tab. (NACA RM L52K13b) 



WIND-TUNNEL INVESTIGATION OF THE STATIC 
LATERAL STABILITY CHARACTERISTICS OF 
WING-FUSELAGE COMBINATIONS AT HIGH SUB- 
SONIC SPEEDS. ASPECT-RATIO SERIES. Paul G. 
Fournier and Andrew L. Byrnes, Jr. February 1953. 
26p. diagrs., photos. (NACA RM L52L18) 

TESTS IN THE AMES 40- BY 80-FOOT WIND TUN- 
NEL OF AN AIRPLANE CONFIGURATION WITH AN 
ASPECT RATIO 3 TRIANGULAR WING AND AN 
ALL-MOVABLE HORIZONTAL TAIL - LONGITU- 
DINAL AND LATERAL CHARACTERISTICS. David 
G. Koenig. April 1953. 61p. diagrs., photos., 
4 tabs. {NACA RM A52L15) 



INVESTIGATION OF THE EFFECTS OF WING AND 
TAIL MODIFICATIONS ON THE LOW -SPEED STA- 
BILITY CHARACTERISTICS OF A MODEL HAVING 
A THIN 40° SWEPT WING OF ASPECT RATIO 3.5. 
Joseph Weil, William C. Sleeman, Jr., and Andrew 
L. Byrnes, Jr. April 1953. 95p. diagrs., photos., 
tab. (NACA RM L53C09) 



97 



(1) AERODYNAMICS 



TESTS IN THE AMES 40- BY 80-FOOT WIND TUN- 
NEL OF AN AIRPLANE CONFIGURATION WITH A 
VARIABLE-INCIDENCE TRIANGULAR WING AND 
AN AL L - MOV AB LE HORI Z ONT AL T AI L. David G. 
Koenig. June 1953. 42p. diagrs., photo., tabs. 
(NACARM A53D21) 



INVESTIGATION AT LOW SPEED OF THE FLOW 
FIELD BEHIND THE LIFTING SURFACES OF A 
MODEL EQUIPPED WITH A 60° TRIANGULAR WING 
AND A 60° TRIANGULAR CANARD TAIL. Ernest E. 
Newman and Jones F. Cahill. June 1953. 44p. 
diagrs., photos., tab. (NACA RM L53C30) 



WIND-TUNNEL INVESTIGATION TO DETERMINE 
THE HORIZONTAL- AND VERTICAL-TAIL CON- 
TRIBUTIONS TO THE STATIC LATERAL STABIL- 
ITY CHARACTERISTICS OF A COMPLETE -MODEL 
SWEPT-WING CONFIGURATION AT HIGH SUBSON- 
IC SPEEDS. James W. Wiggins, Richard E. Kuhn, 
and Paul G, Fournier. July 1953. 34p. diagrs., 
photo. (NACA RM L53E19) 



WIND-TUNNEL INVESTIGATION OF THE EFFECTS 
OF GEOMETRIC DIHEDRAL ON THE AERODYNAM- 
IC CHARACTERISTICS IN PITCH AND SIDESLIP OF 
AN UNSWEPT- AND A 45° SWEPTBACK-WING- 
FUSELAGE COMBINATION AT HIGH SUBSONIC 
SPEEDS. Richard E. Kuhn and John W. Draper. 
July 1953. 41p. diagrs., photos. 
(NACA RM L53F09) 



FREE-FLIGHT -TUNNEL INVESTIGATION OF THE 
LOW-SPEED STABILITY AND CONTROL CHARAC- 
TERISTICS OF A CANARD AIRPLANE MODEL. 

Joseph L. Johnson, Jr., and John W. Paulson. 
October 1953. 37p. diagrs,, photo.. 2 tabs. (NACA 
RM L53I11) 



AN EXPERIMENTAL AND THEORETICAL INVES- 
TIGATION AT HIGH SUBSONIC SPEEDS OF THE 
EFFECTS OF HORIZONTAL-TAIL HEIGHT ON THE 
AERODYNAMIC CHARACTERISTICS IN SIDESLIP 
OF AN UNSWEPT, UNTAPERED TAIL ASSEMBLY. 
Harleth G. Wiley and Donald R. Riley. December 
1953. 71p. diagrs., tab. (NACA RM L53J19) 



STABILITY CHARACTERISTICS AT LOW SPEED OF 
A VARIABLE -SWEEP AIRPLANE MODEL HAVING 
A PARTIALLY CAMBERED WING WITH SEVERAL 
CHORD-EXTENSION CONFIGURATIONS. Robert E. 
Becht. February 1954. 37p. diagrs., photos. 
(NACA RM L53L14) 



PRELIMINARY INVESTIGATION AT SUBSONIC AND 
TRANSONIC SPEEDS OF THE AERODYNAMIC 
CHARACTERISTICS OF A BIPLANE COMPOSED OF 
A SWEPTBACK AND A SWEPTFORWARD WING 
JOINED AT THE TIPS. Jones F. Cahill and 
Dexter H. Stead. March 1954. 19p. diagrs., 
pnotos. (NACA RM L53L24b) 



THE EFFECT OF BLUNT-TRAILING- EDGE MODI- 
FICATIONS ON THE HIGH-SPEED STABILITY AND 
CONTROL CHARACTERISTICS OF A SWEPT-WING 

FIGHTER AIRPLANE. Melvin Sadoff, Frederick H. 
Matteson, and Rudolph D. Van Dyke, Jr. May 1954. 
55p. diagrs., photos., tab. (NACA RM A54C31) 



EFFECTS OF HIGH-LIFT DEVICES AND 
HORIZONTAL-TAIL LOCATION ON THE LOW- 
SPEED CHARACTERISTICS OF A LARGE-SCALE 
45° SWEPT-WING AIRPLANE CONFIGURATION. 
Ralph L. Maki and Ursel R. Embry. August 1954. 
46p. diagrs., photo., tabs. (NACA RM A54E10) 



EFFECTS OF WING POSITION AND FUSELAGE 
SIZE ON THE LOW-SPEED STATIC AND ROLLING 
STABILITY CHARACTERISTICS OF A DELTA-WING 
MODEL. Alex Goodman and David F. Thomas, Jr. 
1955, ii, 31p. diagrs., photos., tabs. 
(NACA Rept. 1224. Supersedes TN 3063) 



THE DYNAMIC-RESPONSE CHARACTERISTICS OF 
A 35° SWEPT-WING AIRPLANE AS DETERMINED 
FROM FLIGHT MEASUREMENTS. William C. 
Triplett, Stuart C. Brown, and G. Allan Smith. 
1955. ii, 25p. diagrs., tabs. (NACA Rept. 1250. 
Supersedes RM A51G27; RM A52I17) 



WIND-TUNNEL INVESTIGATION AT LOW SPEED 
OF EFFECT OF SIZE AND POSITION OF CLOSED 
AIR DUCTS ON STATIC LONGITUDINAL AND 
STATIC LATERAL STABILITY CHARACTERISTICS 
OF UNSWEPT-MIDWING MODELS HAVING WINGS 
OF ASPECT RATIO 2, 4, AND 6. Byron .M. Jaquet 
and James L. Williams. September 1955. 45p. 
diagrs., photos., tabs. (NACA TN 3481) 



THE EFFECTIVENESS OF WING VORTEX GENERA- 
TORS IN IMPROVING THE MANEUVERING CHARAC- 
TERISTICS OF A SWEPT-WING AIRPLANE AT 
TRANSONIC SPEEDS. Norman M. McFadden, 
George A. Rathert, Jr. , and Richard S. Bray. 
September 1955. 43p. diagrs. , photos. , tab. 
(NACA TN 3523. Supersedes RM A51J18) 



LOW-SPEED STATIC LATERAL AND ROLLING 
STABILITY CHARACTERISTICS OF A SERIES OF 
CONFIGURATIONS COMPOSED OF INTERSECTING 
TRIANGULAR PLAN-FORM SURFACES. David F. 
Thomas, Jr. October 1955. 29p. diagrs., photos. 
(NACA TN 3532) 



EXPERIMENTAL INVESTIGATION AT LOW SPEED 
OF EFFECTS OF FUSELAGE CROSS SECTION ON 
STATIC LONGITUDINAL AND LATERAL STABILITY 
CHARACTERISTICS OF MODELS HAVING 0° AND 
45° SWEPTBACK SURFACES. William Letko and 
James L. Williams, December 1955. 45p. diagrs., 
tabs. (NACA TN 3551) 



THEORETICAL SPAN LOAD DISTRIBUTIONS AND 
ROLLING MOMENTS FOR SIDESLIPPING WINGS 
OF ARBITRARY PLAN FORM IN INCOMPRESSIBLE 
FLOW. M. J. Queijo. December 1955. 45p. 
diagrs. (NACA TN 3605) 



WIND-TUNNEL INVESTIGATION OF EFFECTS OF 
FUSELAGE CROSS-SECTIONAL SHAPE, FUSE- 
LAGE BEND, AND VERTICAL-TAIL SIZE ON DI- 
RECTIONAL CHARACTERISTICS OF 
NONOVERLAP-TYPE HELICOPTER FUSELAGE 
MODELS WITHOUT ROTORS. James L. Williams. 
March 1956. 39p. diagrs., photos. 
(NACA TN 3645) 



98 



(1) AERODYNAMICS 



A WIND-TUNNEL INVESTIGATION OF A 0.4-SCALE 
MODEL OF AN ASSAULT-TRANSPORT AIRPLANE 
WITH BOUNDARY-LAYER CONTROL APPLIED. 

Marvin P. Fink, Bonnie W. Cocke, and Stanley 
Lipson. May 1956. 63p. diagrs., photos, 
(NACA RM L55G26a) 

STATIC LONGITUDINAL AND LATERAL STABILITY 
CHARACTERISTICS AT LOW SPEED OF UNSWEPT- 
MIDWING MODELS HAVING WINGS WITH AN 
ASPECT RATIO OF 2, 4, OR 6. Walter D. Wolhart 
and David F. Thomas, Jr. May 1956. 41p. 
diagrs., photos., tabs. (NACA TN 3649) 



(1. 8. 1. 1. 3) 
Directional 

AERODYNAMIC STUDY OF A WING- FUSELAGE 
COMBINATION EMPLOYING A WING SWEPT BACK 
63°. - AERODYNAMIC CHARACTERISTICS IN 
SIDESLIP OF A LARGE-SCALE MODEL HAVING A 
63° SWEPT-BACK VERTICAL TAIL. Gerald M. 
McCormack. October 7, 1949. 26p. diagrs., 
photos. (NACA RM A9F14) 



FLIGHT DETERMINATION OF THE EFFECTS OF 
RUDDER-PEDAL-FORCE CHARACTERISTICS ON 
THE AIMING ERROR IN AZIMUTH OF A CONVEN- 
TIONAL FIGHTER AIRPLANE. Lee Winograd and 
Rudolph D. Van Dyke, Jr. July 5, 1950. 32p. 
diagrs., photos., tab. (NACA RM A50D06) 



EFFECT OF THE PROXIMITY OF THE GROUND ON 
THE STABILITY AND CONTROL CHARACTERIS- 
TICS OF A VERTICALLY RISING AIRPLANE MODEL 
IN THE HOVERING CONDITION. Charles C. Smith, 
Jr., Povvell M. Lovell, Jr., and William R. Bates. 
September 1951. 16p. diagrs., tab. (NACA 
RM L51G05) 



TESTS IN THE AMES 40- BY 80-FOOT WIND TUN- 
NEL OF AN AIRPLANE CONFIGURATION WITH AN 
ASPECT RATIO 2 TRIANGULAR WING AND AN 
ALL-MOVABLE HORIZONTAL TAIL - LATERAL 
CHARACTERISTICS. David Graham and David G. 
Koenig. February 1952. 38p. diagrs., 2 tabs. 
(NACA RM A51L03) 



EFFECT OF CAMBER AND TWIST ON THE STA- 
BILITY CHARACTERISTICS OF MODELS HAVING A 
45° SWEPT WING AS DETERMINED BY THE FREE- 
FALL METHOD AT TRANSONIC SPEEDS. Maurice 
D. White. August 1952. 35p. diagrs., photos., tab. 
(NACA RMA52F16) 



INVESTIGATION OF THE LOW-SPEED AERO- 
DYNAMIC CHARACTERISTICS OF A VARIABLE - 
SWEEP AIRPLANE MODEL WITH A WING HAVING 
PARTIAL-SPAN CAMBERED- LEADING- EDGE 
MODIFICATIONS. Robert E. Becht and Andrew L. 
Byrnes, Jr. September 1952. 47p. diagrs., photos. 
(NACA RM L52G08a) 

TESTS IN THE AMES 40- BY 80 -FOOT WIND TUN- 
NEL OF AN AIRPLANE MODEL WITH AN ASPECT 
RATIO 4 TRIANGULAR WING AND AN ALL- 
MOVABLE HORIZONTAL TAIL - HIGH-LIFT DE- 
VICES AND LATERAL CONTROLS. Ralph W. 
Franks. February 1953. 45p. diagrs., photo.. 2 
tabs. (NACA RM A52K13) 



FLIGHT MEASUREMENTS OF THE STABILITY 
CHARACTERISTICS OF THE BELL X-5 RESEARCH 
AIRPLANE IN SIDESLIPS AT 59° SWEEPBACK. 

Joan M. Childs. February 1953. 23p. diagrs., 
photos., tab. (NACA RM L52K13b) 

WIND-TUNNEL INVESTIGATION OF THE STATIC 
LATERAL STABILITY CHARACTERISTICS OF 
WING-FUSELAGE COMBINATIONS AT HIGH SUB- 
SONIC SPEEDS. ASPECT-RATIO SERIES. Paul G. 
Fournier and Andrew L. Byrnes, Jr. February 1953. 
26p. diagrs.. photos. (NACA RM L52L18} 



TESTS IN THE AMES 40- BY 80-FOOT WEND TUN- 
NEL OF AN AIRPLANE CONFIGURATION WITH AN 
ASPECT RATIO 3 TRIANGULAR WING AND AN 
ALL-MOVABLE HORIZONTAL TAIL - LONGITU- 
DINAL AND LATERAL CHARACTERISTICS. David 
G. Koenig. April 1953. 61p. diagrs., photos., 
4 tabs. (NACA RM A52L15) 



INVESTIGATION OF THE EFFECTS OF WING AND 
TAIL MODIFICATIONS ON THE LOW-SPEED STA- 
BILITY CHARACTERISTICS OF A MODEL HAVING 
A THIN 40° SWEPT WING OF ASPECT RATIO 3.5. 
Joseph Weil, William C. Sleeman, Jr., and Andrew 
L. Byrnes, Jr. April 1953. 95p. diagrs., photos., 
tab. (NACA RM L53C09) 



TESTS IN THE.AMES 40- BY 80-FOOT WIND TUN- 
NEL OF AN AIRPLANE CONFIGURATION WITH A 
VARIABLE-INCIDENCE TRIANGULAR WING AND 
AN ALL-MOVABLE HORIZONTAL TAIL. David G. 
Koenig. June 1953. 42p. diagrs., photo., tabs. 
(NACARM A53D21) 



WIND-TUNNEL INVESTIGATION TO DETERMINE 
THE HORIZONTAL- AND VERTICAL -TAIL CON- 
TRIBUTIONS TO THE STATIC LATERAL STABIL- 
ITY CHARACTERISTICS OF A COMPLETE -MODEL 
SWEPT-WING CONFIGURATION AT HIGH SUBSON- 
IC SPEEDS. James W. Wiggins, Richard E. Kuhn, 
and Paul G. Fournier. July 1953. 34p. diagrs., 
photo. (NACA RM L53E1D) 



WIND-TUNNEL INVESTIGATION OF THE EFFECTS 
OF GEOMETRIC DIHEDRAL ON THE AERODYNAM- 
IC CHARACTERISTICS IN PITCH AND SIDESLIP OF 
AN UNSWEPT- AND A 45° SWEPTBACK-WING- 
FUSELAGE COMBINATION AT HIGH SUBSONIC 
SPEEDS. Richard E. Kuhn and John W. Draper. 
July 1953. 41p. diagrs., photos. 
(NACA RM L53F09) 



FREE-FLIGHT -TUNNEL INVESTIGATION OF THE 
LOW-SPEED STABILITY AND CONTROL CHARAC- 
TERISTICS OF A CANARD AIRPLANE MODEL. 
Joseph L. Johnson, Jr., and John W. Paulson. 
October 1953. 37p. diagrs., photo., 2 tabs. (NACA 
RM L53I11) 



AN EXPERIMENTAL AND THEORETICAL INVES- 
TIGATION AT HIGH SUBSONIC SPEEDS OF THE 
EFFECTS OF HORIZONTAL-TAIL HEIGHT ON THE 
AERODYNAMIC CHARACTERISTICS IN SIDESLIP 
OF AN UNSWEPT, UNTAPERED TAIL ASSEMBLY. 
Harleth G. Wiley and Donald R. Riley. December 
1953. 71p. diagrs., tab. (NACA RM L53J19) 



99 



(1) AERODYNAMICS 



A STUDY OF THE CHARACTERISTICS OF HUMAN- 
PILOT CONTROL RESPONSE TO SIMULATED AIR- 
CRAFT LATERAL MOTIONS. Donald C. Cheatham. 
1954. ii, 14p. diagrs., photos., tab. (NACA 
Rept. 1197. Formerly RM L52C17) 



STABILITY CHARACTERISTICS AT LOW SPEED OF 
A VARIABLE -SWEEP AIRPLANE MODEL HAVING 
A PARTIALLY CAMBERED WING WITH SEVERAL 
CHORD-EXTENSION CONFIGURATIONS. Robert E. 
Becht. February 1954. 37p. diagrs., photos. 
(NACA RM L53L14) 



CHARTS FOR ESTIMATING TAIL-ROTOR CONTRI- 
BUTION TO HELICOPTER DIRECTIONAL STABIL- 
ITY AND CONTROL IN LOW-SPEED FLIGHT. 
Kenneth B. Amer and Alfred Gessow. 1955. ii, 
22p. diagrs., photo., tabs. (NACA Rept. 1216. 
Supersedes TN 3156) 



EFFECTS OF WING POSITION AND FUSELAGE 
SIZE ON THE LOW-SPEED STATIC AND ROLLING 
STABILITY CHARACTERISTICS OF A DELTA-WING 
MODEL. Alex Goodman and David F. Thomas, Jr. 
1955. ii, 31p. diagrs., photos., tabs. 
(NACA Rept. 1224. Supersedes TN 3063) 



THE DYNAMIC -RESPONSE CHARACTERISTICS OF 
A 35° SWEPT-W1NG AIRPLANE AS DETERMINED 
FROM FLIGHT MEASUREMENTS. William C. 
Triplett, Stuart C. Brown, and G. Allan Smith. 
1955. ii, 25p. diagrs., tabs. (NACA Rept. 1250. 
Supersedes RM A51G27; RM A52I17) 



WIND-TUNNEL INVESTIGATION AT LOW SPEED 
OF EFFECT OF SIZE AND POSITION OF CLOSED 
AIR DUCTS ON STATIC LONGITUDINAL AND 
STATIC LATERAL STABILITY CHARACTERISTICS 
OF UNSWEPT-MIDWING MODELS HAVING WINGS 
OF ASPECT RATIO 2, 4, AND 6. Byron M. Jaquet 
and James L. Williams. September 1955. 45p. 
diagrs., photos., tabs. (NACA TN 3481) 



LOW-SPEED STATIC LATERAL AND ROLLING 
STABILITY CHARACTERISTICS OF A SERIES OF 
CONFIGURATIONS COMPOSED OF INTERSECTING 
TRIANGULAR PLAN-FORM SURFACES. David F. 
Thomas, Jr. October 1955. 29p. diagrs., photos. 
(NACA TN 3532) 



EXPERIMENTAL INVESTIGATION AT LOW SPEED 
OF EFFECTS OF FUSELAGE CROSS SECTION ON 
STATIC LONGITUDINAL AND LATERAL STABILITY 
CHARACTERISTICS OF MODELS HAVING 0° AND 
45° SWEPTBACK SURFACES. William Letko and 
James L. Williams. December 1955. 45p. diagrs., 
tabs. (NACA TN 3551) 



WIND-TUNNEL INVESTIGATION OF EFFECTS OF 
FUSELAGE CROSS-SECTIONAL SHAPE, FUSE- 
LAGE BEND, AND VERTICAL-TAIL SIZE ON DI- 
RECTIONAL CHARACTERISTICS OF 
NONOVERLAP-TYPE HELICOPTER FUSELAGE 
MODELS WITHOUT ROTORS. James L. Williams. 
March 1956. 39p. diagrs., photos. 
(NACA TN 3645) 



STATIC LONGITUDINAL AND LATERAL STABILITY 
CHARACTERISTICS AT LOW SPEED OF UNSWEPT- 
MIDWING MODELS HAVING WINGS WITH AN 
ASPECT RATIO OF 2, 4, OR 6. Walter D. Wolhart 
and David F. Thomas, Jr. May i9S6. 4ip. 
diagrs., photos., tabs. (NACA TN 3649) 



(1.8. 1. 2) 
DYNAMIC 



EXPERIMENTAL DAMPING IN PITCH OF 45° TRI- 
ANGULAR WINGS. Murray Tobak, David E. Reese, 
Jr., and Benjamin H. Beam. December 1, 1950. 
63p. diagrs., photo. (NACA RM A50J26) 



FLIGHT INVESTIGATION OF A ROLL-STABILIZED 
MISSILE CONFIGURATION AT VARYING ANGLES 
OF ATTACK AT MACH NUMBERS BETWEEN 0.8 
AND 1.79. Jacob Zarovsky and Robert A. Gardiner. 
March 6, 1951. 38p. diagrs., photos., tab, 
(NACA RM L50H21) 



ADDITIONAL STUDIES OF THE STABILITY AND 
CONTROLLABILITY OF AN UNSWEPT-WING 
VERTICALLY RISING AIRPLANE MODEL IN 
HOVERING FLIGHT INCLUDING STUDIES OF VAR- 
IOUS TETHERED LANDING TECHNIQUES. 
William R. Bates. Powell M. Lovell, Jr., and 
Charles C. Smith, Jr. November 1951. 25p. 
diagrs., photos., tab. (NACA RM L51I07a) 



ON THE USE OF THE INDICIAL FUNCTION CON- 
CEPT IN THE ANALYSIS OF UNSTEADY MOTIONS 
OF WINGS AND WING-TAIL COMBINATIONS. 
Murray Tobak. 1954. iii, 43p. diagrs. (NACA 
Rept. 1188) 



LABORATORY INVESTIGATION OF AN AUTOPILOT 
UTILIZING A MECHANICAL LINKAGE WITH A 
DEAD SPOT TO OBTAIN AN EFFECTIVE RATE 
SIGNAL. Ernest C. Seaberg. December 1955. 27p. 
diagrs., photos., tab. (NACA TN 3602. Supersedes 
RM L9F15a) 



HOVERING-FLIGHT TESTS OF A MODEL OF A 
TRANSPORT VERTICAL-TAKE-OFF AIRPLANE 
WITH TILTING WING AND PROPELLERS. Powell 
M. Lovell, Jr., and Lysle P. Parlett. March 1956. 
23p diagrs., photo., tab. (NACA TN 3630) 



(1.8. 1. 2. 1) 
Longitudinal 

AERODYNAMIC CHARACTERISTICS AND FLYING 
QUALITIES OF A TAILLESS TRIANGULAR-WING 
AIRPLANE CONFIGURATION AS OBTAINED FROM 
FLIGHTS OF ROCKET -PROPELLED MODELS AT 
TRANSONIC AND LOW SUPERSONIC SPEEDS. 
Grady L. Mitcham, Joseph E. Stevens, and Harry P. 
Norris. February 9, 1950. 67p. diagrs., photos., 
tabs. (NACA RM L9L07) 



100 



(1) AERODYNAMICS 



THE LONGITUDINAL STABILITY, CONTROL EF- 
FECTIVENESS AND CONTROL HINGE-MOMENT 
CHARACTERISTICS OBTAINED FROM A FLIGHT 
INVESTIGATION OF A CANARD MISSILE CONFIG- 
URATION AT TRANSONIC AND SUPERSONIC 
SPEEDS. Roy J. Niewald and Martin T. Moul. 
November 24, 1950. 43p. diagrs., photos. 
(NACA RM L50I27) 



EXPERIMENTAL DAMPING IN PITCH OF 45° TRI- 
ANGULAR WINGS. Murray Tobak, David E. Reese, 
Jr., and Benjamin H. Beam. December 1, 1950. 
63p. diagrs., photo. (NACA RM A50J26) 



DYNAMIC STABILITY AND CONTROL CHARACTER- 
ISTICS OF A VERTICALLY RISING AIRPLANE 
MODEL IN HOVERING FLIGHT. William R. Bates, 
Powell M. Lovell, Jr., and Charles C. Smith, Jr. 
February 23, 1951. 16p. diagrs., photos., tab. 
(NACA RM L50J16) 



DYNAMIC STABILITY AND CONTROL CHARACTER- 
ISTICS OF A DELTA-WING VERTICALLY RISING 
AIRPLANE MODEL IN TAKE-OFFS, LANDINGS, 
AND HOVERING FLIGHT. Powell M. Lovell, Jr., 
William R. Bates and Charles C. Smith, Jr. 
October 1951. 14p. diagrs., photo., tab. (NACA 
RM L51H13a) 



LONGITUDINAL STABILITY AND CONTROL CHAR- 
ACTERISTICS FROM A FLIGHT INVESTIGATION 
OF A CRUCIFORM CANARD MISSILE CONFIGURA- 
TION HAVING AN EXPOSED WING-CANARD AREA 
RATIO OF 16:1. Martin T. Moul and Andrew R. 
Wineman. June 1952. 32p. diagrs., photos. 
(NACARML52D24a) 



EFFECT OF CAMBER AND TWIST ON THE STA- 
BILITY CHARACTERISTICS OF MODELS HAVING A 
45° SWEPT WING AS DETERMINED BY THE FREE- 
FALL METHOD AT TRANSONIC SPEEDS. Maurice 
D. White. August 1952. 35p. diagrs., photos., tab. 
(NACA RMA52F16) 



LONGITUDINAL STABILITY, TRIM. AND DRAG 
CHARACTERISTICS OF A ROCKET-PROPELLED 
MODEL OF AN AIRPLANE CONFIGURATION HAV- 
ING A 45° SWEPTBACK WING AND AN UNSWEPT 
HORIZONTAL TAIL, James H. Parks and Alan B. 
Kehlet. August 1952. 29p. diagrs., photos., tab. 
(NACA RM L52FG5) 



LONGITUDINAL STABILITY AND CONTROL CHAR- 
ACTERISTICS OF A CANARD MISSILE CONFIGURA- 
TION FOR MACH NUMBERS FROM 1.1 TO 1.93 AS 
DETERMINED FROM FREE-FLIGHT AND WIND- 
TUNNEL INVESTIGATIONS. Howard J. Curfman, 
Jr., and Carl E. Grigsby. August 1952. 28p. 
diagrs., tab. (NACA RM L52F06) 



FREE-FLIGHT -TUNNEL INVESTIGATION OF THE 
LOW-SPEED STABILITY AND CONTROL CHARAC- 
TERISTICS OF A CANARD AIRPLANE MODEL. 
Joseph L. Johnson, Jr., and John W. Paulson. 
October 1953. 37p. diagrs., photo., 2 tabs. (NACA 
RM L53I11) 



ON THE USE OF THE INDICIA L FUNCTION CON- 
CEPT IN THE ANALYSIS OF UNSTEADY MOTIONS 
OF WINGS AND WING-TAIL COMBINATIONS. 
Murray Tobak. 1954. iii, 43p. diagrs. (NACA 
Rept. 1188) 



APPLICATION OF SEVERAL METHODS FOR DE- 
TERMINING TRANSFER FUNCTIONS AND FRE- 
QUENCY RESPONSE OF AIRCRAFT FROM FLIGHT 

DATA. John M. Eggleston and Charles W. 
Mathews. 1954. ii, 24p. diagrs., tabs. 
(NACA Rept. 1204. Supersedes TN 2997) 



FLIGHT TESTS OF A 0.4-SCALE MODEL OF A 
STAND-ON TYPE OF VERTICALLY RISING AIR- 
CRAFT. Marion O. McKinney and Lysle P. Parlett. 
March 1954. 23p. diagrs., photos. (NACA 
RM L54B16b) 



DYNAMIC STABILITY AND CONTROL CHARACTER- 
ISTICS OF A DUCTED-FAN MODEL IN HOVERING 
FLIGHT. Robert H. Kirby. April 1954. 16p. 
diagrs., photos. (NACA RM L54C18) 



THEORETICAL AND ANALOG STUDIES OF THE 
EFFECTS OF NONLINEAR STABILITY DERIVA- 
TIVES ON THE LONGITUDINAL MOTIONS OF AN 
AIRCRAFT IN RESPONSE TO STEP CONTROL 
DEFLECTIONS AND TO THE INFLUENCE OF PRO- 
PORTIONAL AUTOMATIC CONTROL. Howard J. 
Curfman, Jr. 1955. il, 21p. diagrs. (NACA 
Rept. 1241. Supersedes RM L50L11) 



THE DYNAMIC-RESPONSE CHARACTERISTICS OF 
A 35° SWEPT-WING AIRPLANE AS DETERMINED 
FROM FLIGHT MEASUREMENTS. William C. 
Triplett, Stuart C. Brown, and G. Allan Smith. 
1955. ii, 25p. diagrs., tabs. (NACA Rept. 1250. 
Supersedes RM A51G27; RM A52I17) 



FLIGHT DETERMINATION OF THE LONGITUDINAL 
STABILITY AND CONTROL CHARACTERISTICS OF 
THE BELL X-5 RESEARCH AIRPLANE AT 58. 7° 
SWEEPBACK. Thomas W. Finch. May 1955. 30p. 
diagrs., photo., tab. (NACA RM H55C07) 



FLIGHT MEASUREMENTS OF THE DYNAMIC 
LATERAL AND LONGITUDINAL STABILITY OF 
THE BELL X-5 RESEARCH AIRPLANE AT 58.7° 
SWEEPBACK. Edward N. Videan. October 1955. 
68p. diagrs., photo., tabs. (NACA RM H55H10) 



SOME EFFECTS OF FUSELAGE FLEXIBILITY ON 
LONGITUDINAL STABILITY AND CONTROL. 
Bernard B. Klawans and Harold I. Johnson. April 
1956. 42p. diagrs., tab. (NACA TN 3543) 



ANALYSIS OF A VANE-CONTROLLED GUST- 
ALLEVIATION SYSTEM. Robert W. Boucher and 
Christopher C. Kraft, Jr. April 1956. 45p. 
diagrs., tabs. (NACA TN 3597) 



101 



(1) AERODYNAMICS 



(1.8. 1.2.2) 
Lateral and Directional 



PRELIMINARY THEORETICAL AND FLIGHT IN- 
VESTIGATION OF THE LATERAL OSCILLATION 
OF THE X-l AIRPLANE. Hubert M. Drake and 
Helen L. Wall. July 19, 1949. 24p, diagrs., photo., 
tab. (NACA KM L9F07) 



FLIGHT DETERMINATION OF THE EFFECTS OF 
RUDDER-PEDAL-FORCE CHARACTERISTICS ON 
THE AIMING ERROR IN AZIMUTH OF A CONVEN- 
TIONAL FIGHTER AIRPLANE. Lee Winograd and 
Rudolph D. Van Dyke, Jr. July 5, 1950. 32p. 
diagrs., photos., tab. (NACA RM A50D06) 



DYNAMIC STABILITY AND CONTROL CHARACTER- 
ISTICS OF A VERTICALLY RISING AIRPLANE 
MODEL IN HOVERING FLIGHT. William R. Bates, 
Po-vell M. Lovell, Jr., and Charles C. Smith, Jr. 
February 23, 1951. 16p. diagrs., photos., tab. 
(NACA RM L50J16) 



EFFECT OF THE PROXIMITY OF THE GROUND ON 
THE STABILITY AND CONTROL CHARACTERIS- 
TICS OF A VERTICALLY RISING AIRPLANE MODEL 
IN THE HOVERING CONDITION. Charies C. Smith, 
Jr., Powell M. Lovell, Jr., and William R. Bates. 
September 1951. 16p. diagrs., tab. (NACA 
RM L51G05) 



DYNAMIC STABILITY AND CONTROL CHARACTER- 
ISTICS OF A DELTA-WING VERTICALLY RISING 
AIRPLANE MODEL IN TAKE-OFFS, LANDINGS, 
AND HOVERING FLIGHT. Powell M. Lovell, Jr., 
William R. Bates and Charles C. Smith, Jr. 
October 1951. 14p. diagrs., photo., tab. (NACA 
RM L5lH13a) 



AN APPROXIMATION TO THE EFFECT OF GEO- 
METRIC DIHEDRAL ON THE ROLLING MOMENT 
DUE TO SIDESLIP FOR WINGS AT TRANSONIC AND 
SUPERSONIC SPEEDS. Paul E. Purser. April 
1952. lOp. diagrs. (NACA RM L52B01) 



PRELIMINARY THEORETICAL INVESTIGATION OF 
SEVERAL METHODS FOR STABILIZING THE 
LATERAL MOTION OF A HIGH-SPEED FIGHTER 
AIRPLANE TOWED BY A SINGLE CABLE. 
Albert A. Schy and Carroll H, Woodling. March 
1953. 46p. diagrs., 2 tabs. (NACA RM L52L24) 



FREE-FLIGHT-TUNNEL INVESTIGATION OF THE 
LOW-SPEED STABILITY AND CONTROL CHARAC- 
TERISTICS OF A CANARD AIRPLANE MODEL. 
Joseph L. Johnson, Jr., and John W. Paulson. 
October 1953. 37p. diagrs., photo., 2 tabs. (NACA 
RM L53I11) 



A STUDY OF THE CHARACTERISTICS OF HUMAN- 
PILOT CONTROL RESPONSE TO SIMULATED AIR- 
CRAFT LATERAL MOTIONS. Donald C. Cheatham. 
1954. ii, 14p. diagrs., photos., tab. (NACA 
Rept. 1197. Formerly RM L52C17) 



A STUDY OF THE PROBLEM OF DESIGNING AIR- 
PLANES WITH SATISFACTORY INHERENT DAMP- 
ING OF THE DUTCH ROLL OSCILLATION. John P. 
Campbell and Marion O. McKinney, Jr. 1954. ii, 
lop. diagrs., tabs. (NACA Rept. 1199. Super- 
sedes TN 3035) 



FLIGHT TESTS OF A 0.4-SCALE MODEL OF A 
STAND-ON TYPE OF VERTICALLY RISING AIR- 
CRAFT. Marion O. McKinney and Lysle P. Parlett. 
March 1954. 23p. diagrs., photos. (NACA 
RM L54B16b) 



THEORETICAL INVESTIGATION OF SOME DISCON- 
TINUOUS YAW DAMPERS. William H. Phillips and 
Helmut A. Kuehnel. April 1954. 39p. diagrs. 
(NACARM L54B24a) 



DYNAMIC STABILITY AND CONTROL CHARACTER- 
ISTICS OF A DUCTED-FAN MODEL IN HOVERING 

FLIGHT. Robert H. Kirby. April 1954. 16p. 
diagrs., photos. (NACA RM L54C18) 



CHARTS FOR ESTIMATING TAIL-ROTOR CONTRI- 
BUTION TO HELICOPTER DIRECTIONAL STABIL- 
ITY AND CONTROL IN LOW-SPEED FLIGHT. 
Kenneth B. Amer and Alfred Gessow. 1955. ii, 
22p. diagrs., photo., tabs. (NACA Rept. 1216. 
Supersedes TN 3156) 



EFFECTS OF WING POSITION AND FUSELAGE 
SIZE ON THE LOW-SPEED STATIC AND ROLLING 
STABILITY CHARACTERISTICS OF A DELTA-WING 
MODEL. Alex Goodman and David F. Thomas, Jr. 
1555. ii, 31p. diagrs., photos., tabs. 
(NACA Rept. 1224. Supersedes TN 3063) 



DETERMINATION OF LATERAL-STABILITY DE- 
RIVATIVES AND TRANSFER -FUNCTION COEFFI- 
CIENTS FROM FREQUENCY-RESPONSE DATA FOR 
LATERAL MOTIONS. James J. Donegan, Samuel 
W. Robinson, Jr., and Ordway B. Gates, Jr. 1955. 
i, 19p. diagrs., tabs. (NACA Rept. 1225. Super- 
sedes TN 3083) 



THE DYNAMIC -RESPONSE CHARACTERISTICS OF 
A 35° SWEPT- WING AIRPLANE AS DETERMINED 
FROM FLIGHT MEASUREMENTS. William C. 
Triplett, Stuart C. Brown, and G. Allan Smith. 
1955. ii, 25p. diagrs., tabs. (NACA Rept. 1250. 
Supersedes RM A51G27; RM A52I17) 



A COMPARISON OF THE MEASURED AND PRE- 
DICTED LATERAL OSCILLATORY CHARACTERIS- 
TICS OF A 35° SvVEPT-WING FIGHTER AIRPLANE. 

vValter E. McNeill and George E. Cooper. August 
1955. 22p. diagrs., photo., 3 tabs. (NACA 
TN 3521. Formerly RM A51C28) 



FLIGHT MEASUREMENTS OF THE DYNAMIC 
LATERAL AND LONGITUDINAL STABILITY OF 
THE BELL X-5 RESEARCH AIRPLANE AT 58.7° 
SWEEPBACK. Edward N. Videan. October 1955. 
68p. diagrs., photo., tabs. (NACA RM H55H10) 



102 



(1) AERODYNAMICS 



LOW-SPEED STATIC LATERAL AND ROLLING 
STABILITY CHARACTERISTICS OF A SERIES OF 
CONFIGURATIONS COMPOSED OF INTERSECTING 
TRIANGULAR PLAN-FORM SURFACES. David F. 
Thomas, Jr. October 1955. 29p. diagrs., photos. 
(NACA TN 3532) 



DIRECTIONAL STABILITY OF TOWED AIRPLANES. 
(Die Seitenstabilitat eines geschieppten Flugzeuges). 
W. Sohne. January 1956. 53p. diagrs., tab. 
(NACA TM 1401. Trans, from Ingenieur-Archiv, 
v.21, no. 4, 1953, p. 245-265) 



A PRELIMINARY INVESTIGATION OF THE EF- 
FECTS OF FREQUENCY AND AMPLITUDE ON THE 
ROLLING DERIVATIVES OF AN UNSWEPT-WTNG 
MODEL OSCILLATING IN ROLL. Lewis R. Fisher, 
Jacob H. Lichtenstein, and Katherine D. Williams. 
January 1956, 29p. diagrs., photos. 
(NACA TN 3554) 



THEORETICAL STUDY OF THE LATERAL FRE- 
QUENCY RESPONSE TO GUSTS OF A FIGHTER AIR- 
PLANE, BOTH WITH CONTROLS FLXED AND WITH 
SEVERAL TYPES OF AUTOPILOTS. James J. 
Adams and Charles W. Mathews. March 1956. 46p. 
diagrs., tabs. (NACA TN 3603) 



LINEARIZED LIFTING-SURFACE AND LIFTING- 
LINE EVALUATIONS OF SIDEWASH BEHIND 
ROLLING TRIANGULAR WINGS AT SUPERSONIC 
SPEEDS. Percy J. Bobbitt. March 1956. 63p. 
diagrs. (NACA TN 3609) 



ANALYTICAL STUDY OF MODIFICATIONS TO THE 
AUTOPILOT OF A FIGHTER AIRPLANE IN ORDER 
TO REDUCE THE RESPONSE TO SIDE GUSTS. 
Charles W. Mathews and James J. Adams. March 
1956. 35p. diagrs., tabs. (NACA TN 3635) 



FLIGHT INVESTIGATION OF THE EFFECTIVENESS 
OF AN AUTOMATIC AILERON TRIM CONTROL 
DEVICE FOR PERSONAL AIRPLANES. William H. 
Phillips, Helmut A. Kuehnel and James B. Whitten. 
April 1956. 42p. diagrs., photos., tab. 
(NACA TN 3637) 



(1. 8. 1. 2. 3) 
Damping Derivatives 

FREE-FLIGHT INVESTIGATION OF THE ROLLING 
EFFECTIVENESS OF SEVERAL DELTA WING - 
AILERON CONFIGURATIONS AT TRANSONIC AND 
SUPERSONIC SPEEDS. Carl A. Sandahl. 
August 27, 1948. 19p. diagrs., photos., tab. 
(NACA RM L8D16) 



PRELIMINARY THEORETICAL AND FLIGHT IN- 
VESTIGATION OF THE LATERAL OSCILLATION 

OF THE X-l AIRPLANE. Hubert M. Drake and 
Helen L. Wall. July 19, 1049. 24p. diagrs., photo 
tab. (NACA RM L9F07) 



ROCKET-POWERED FLIGHT TEST OF A ROLL- 
STABILIZED SUPERSONIC MISSILE CONFIGURA- 
TION. Robert A. Gardiner and Jacob Zarovsky. 
January 12, 1950. 32p. diagrs., photos., tab. 
(NACA RM L9K01a) 



AERODYNAMIC CHARACTERISTICS AND FLYING 
QUALITIES OF A TAILLESS TRIANGULAR-WING 
AIRPLANE CONFIGURATION AS OBTAINED FROM 
FLIGHTS OF ROCKET-PROPELLED MODELS AT 
TRANSONIC AND LOW SUPERSONIC SPEEDS. 
Grady L. Mitcham, Joseph E. Stevens, and Harry P. 
Norris. February 9, 1950. 67p. diagrs,, photos., 
tabs. (NACA RM L9L07) 



EXPERIMENTAL DAMPING IN PITCH OF 45° TRI- 
ANGULAR WINGS. Murray Tobak, David E. Reese, 
Jr., and Benjamin H. Beam. December 1, 1950. 
63p. diagrs., photo. (NACA RM A50J26) 



WIND-TUNNEL INVESTIGATION AT SUBSONIC AND 
LOW TRANSONIC SPEEDS OF THE EFFECTS OF 
AILERON SPAN AND SPANWTSE LOCATION ON THE 
ROLLING CHARACTERISTICS OF A TEST VEHICLE 
WITH THREE UNTAPERED 45° SWEPTBACK 
WINGS. HaroldS. Johnson. April 6, 1951. 26p. 
diagrs., photo., tab. (NACA RM L51B16) 



SOME EFFECTS OF FUSELAGE INTERFERENCE, 
WING INTERFERENCE AND SWEEPBACK ON THE 
DAMPING IN ROLL OF UNTAPERED WINGS AS DE- 
TERMINED BY TECHNIQUES EMPLOYING 
ROCKET-PROPELLED VEHICLES. William M. 
Bland, Jr., and Albert E. Dietz. October 1951, 27p. 
diagrs., photos. (NACA RM L51D25) 

DAMPING IN ROLL OF STRAIGHT AND 45° SWEPT 
WINGS OF VARIOUS TAPER RATIOS DETERMINED 
AT HIGH SUBSONIC, TRANSONIC, AND SUPER- 
SONIC SPEEDS WITH ROCKET -POWERED 
MODELS. E. Claude Sanders, Jr. October 1951. 
15p. diagrs. (NACA RM L51H14) 

DAMPING IN ROLL OF MODELS WITH 45°, 60°, 
AND 70° DELTA WINGS DETERMINED AT HIGH 
SUBSONIC, TRANSONIC, AND SUPERSONIC 
SPEEDS WITH ROCKET-POWERED MODELS. 
E. Claude Sanders, Jr. June 1952. 18p. diagrs., 
photos. (NACA RM L52D22a) 

EFFECT OF FUSELAGE INTERFERENCE ON THE 
DAMPING IN ROLL OF DELTA WINGS OF ASPECT 
RATIO 4 IN THE MACH NUMBER RANGE BETWEEN 
0.6 AND 1.6 AS DETERMINED WITH ROCKET- 
PROPELLED VEHICLES. William M. Bland, Jr. 
July 1952. 13p. diagrs., photos. (NACA RM L52E13) 

EFFECT OF CAMBER AND TWIST ON THE STA- 
BILITY CHARACTERISTICS OF MODELS HAVING A 
45° SWEPT WING AS DETERMINED BY THE FREE- 
FALL METHOD AT TRANSONIC SPEEDS. Maurice 
D. White. August 1952. 35p. diagrs., photos., tab. 
(NACA RM A52F16) 

LONGITUDINAL STABILITY, TRIM, AND DRAG 
CHARACTERISTICS OF A ROCKET-PROPELLED 
MODEL OF AN AIRPLANE CONFIGURATION HAV- 
ING A 45° SWEPTBACK WING AND AN UNSWEPT 
HORIZONTAL TAIL. James H. Parks and Alan B. 
Kehlct. August 1952. 29p. diagrs., photos., tab. 
(NACA RM L52F05) 



103 



(1) AERODYNAMICS 



INVESTIGATIONS OF THE DAMPING IN ROLL OF 
SWEPT AND TAPERED WINGS AT SUPERSONIC 
SPEEDS. Russell W. McDearmon and Harry S. 
Heinke, Jr. March 1953. 35p. diagrs., photos., 
tab. (NACA RM L53A13) 



A COLLECTION OF DATA FOR ZERO-LIFT DAMP- 
ING IN ROLL OF WING-BODY COMBINATIONS AS 
DETERMINED WITH ROCKET-POWERED MODELS 
EQUIPPED WITH ROLL-TORQUE NOZZLES. 
David G. Stone. July 1953. 23p. diagrs., tab. 
{NACA RM L53E26) 



FREE-FLIGHT -TUNNEL INVESTIGATION OF THE 
LOW-SPEED STABILITY AND CONTROL CHARAC- 
TERISTICS OF A CANARD AIRPLANE MODEL. 

Joseph L. Johnson, Jr., and John W. Paulson. 
October 1953. 37p. diagrs., photo., 2 tabs. (NACA 
RM L53I11) 



WIND-TUNNEL INVESTIGATION OF THE EFFECTS 
OF STEADY ROLLING ON THE AERODYNAMIC 
LOADING CHARACTERISTICS OF A 45° SWEPT- 
BACK WING AT HIGH SUBSONIC SPEEDS. James 
W. Wiggins and Richard E. Kuhn. November 1953. 
22p. diagrs., photos. (NACA RM L53J01a) 



SUPERSONIC FLOW PAST OSCILLATING AIRFOILS 

INCLUDING NONLINEAR THICKNESS EFFECTS. 
Milton D. Van Dyke. 1954. ii, 17p. diagrs. (NACA 
Rept. 1183. Formerly TN 2982) 



ON THE USE OF THE INDICIAL FUNCTION CON- 
CEPT IN THE ANALYSIS OF UNSTEADY MOTIONS 
OF WINGS AND WING-TAIL COMBINATIONS. 

Murray Tobak. 1954. iii, 43p. diagrs. (NACA 
Rept. 1188) 



EFFECTS OF WING POSITION AND FUSELAGE 
SIZE ON THE LOW-SPEED STATIC AND ROLLING 
STABILITY CHARACTERISTICS OF A DELTA -WING 
MODEL. Alex Goodman and David F. Thomas, Jr. 
1955. ii, 31p. diagrs., photos., tabs. 
(NACA Rept. 1224. Supersedes TN 3063) 



THEORETICAL AND ANALOG STUDIES OF THE 
EFFECTS OF NONLINEAR STABILITY DERIVA- 
TIVES ON THE LONGITUDINAL MOTIONS OF AN 
AIRCRAFT IN RESPONSE TO STEP CONTROL 
DEFLECTIONS AND TO THE INFLUENCE OF PRO- 
PORTIONAL AUTOMATIC CONTROL. Howard J. 
Curfman, Jr. 1955. ii, 21p. diagrs. (NACA 
Rept. 1241. Supersedes RM L50L11) 



THE DYNAMIC-RESPONSE CHARACTERISTICS OF 
A 35° SWEPT-WING AIRPLANE AS DETERMINED 
FROM FLIGHT MEASUREMENTS. William C. 
Triplett, Stuart C. Brown, and G. Allan Smith. 
1955. ii, 25p. diagrs., tabs. (NACA Rept. 1250. 
Supersedes RM A51G27; RM A52U7) 



AERODYNAMICS OF A RECTANGULAR WING OF 
INFINITE ASPECT RATIO AT HIGH ANGLES OF 
ATTACK AND SUPERSONIC SPEEDS. John C. 
Martin and Frank S. Malvestuto, Jr. July 1955. 
114p. diagrs., tab. (NACA TN 3421) 



LOW-SPEED STATIC LATERAL AND ROLLING 
STABILITY CHARACTERISTICS OF A SERIES OF 
CONFIGURATIONS COMPOSED OF INTERSECTING 
TRIANGULAR PLAN-FORM SURFACES. David F. 
Thomas, Jr. October 1955. 29p. diagrs., photos. 
(NACA TN 3532) 



A PRELIMINARY INVESTIGATION OF THE EF- 
FECTS OF FREQUENCY AND AMPLITUDE ON THE 
ROLLING DERTVATIVES OF AN UNSWEPT-WTNG 
MODEL OSCILLATING IN ROLL. Lewis R. Fisher, 
Jacob H. Lichtenstein, and Katherine D. Williams. 
January 1956. 29p. diagrs., photos. 
(NACA TN 3554) 



LINEARIZED LIFTING-SURFACE AND LIFTING- 
LINE EVALUATIONS OF SIDEWASH BEHIND 
TROLLING TRIANGULAR WINGS AT SUPERSONIC 
SPEEDS. Percy J. Bobbitt. March 1956. 63p. 
diagrs. (NACA TN 3609) 



EXPERIMENTAL MEASUREMENTS OF FORCES 
AND MOMENTS ON A TWO-DIMENSIONAL OSCIL- 
LATING WING AT SUBSONIC SPEEDS. Sherman A. 
Clevenson and Edward Widmayer, Jr. June 1956. 
28p. diagrs., tab. (NACA TN 3686. Supersedes 
RM L9K28a) 



PRELIMINARY WIND-TUNNEL TESTS OF TRIAN- 
GULAR AND RECTANGULAR WINGS IN STEADY 
ROLL AT MACH NUMBERS OF 1.62 AND 1.92. 
Clinton E. Brown and Harry S. Heinke, Jr. 
June 1956. 36p. diagrs., tabs. 
(NACA TN 3740. Supersedes RM L8L30) 



(1.8.2) 
CONTROL 



ADDITIONAL STUDIES OF THE STABILITY AND 
CONTROLLABILITY OF AN UNSWEPT-WING 
VERTICALLY RISING AIRPLANE MODEL IN 
HOVERING FLIGHT INCLUDING STUDIES OF VAR- 
IOUS TETHERED LANDING TECHNIQUES. 
William R. Bates, Powell M. Loveli, Jr., and 
Charles C. Smith, Jr. Movember 1951. 25p. 
diagrs., photos., tab. (NACA RM L51I07a) 



PRELIMINARY DATA AT A MACH NUMBER OF 2.40 
OF THE CHARACTERISTICS OF FLAP-TYPE CON- 
TROLS EQUIPPED WITH PLAIN OVERHANG BAL- 
ANCES. James N. Mueller and K. R. Czarnecki. 
September 1952. 43p. diagrs., photos. 
(NACARM L52F10) 



FLIGHT TESTS OF A 0.4-SCALE MODEL OF A 
STAND-ON TYPE OF VERTICALLY RISING AIR- 
CRAFT. Marion O. McKinney and Lysle P. Parlett. 
March 1954. 23p. diagrs., photos. (NACA 
RM L54B16b) 



LARGE-SCALE LOW -SPEED WIND-TUNNEL TESTS 
OF A MODEL HAVING A 60° DELTA HORIZONTAL 
CANARD CONTROL SURFACE AND WING TO OB- 
TAIN STATIC-LONGITUDINAL-STABILITY AND 
CANARD-SURFACE HINGE-MOMENT DATA. 
Dale L. Burrows. June 1954. 21p. diagrs. 
(NACA RM L54D16a) 



104 



(1) AERODYNAMICS 



(1. 8. 2. 1) 
LONGITUDINAL 



LOW-SPEED WIND-TUNNEL TESTS OF A PILOT- 
LESS AIRCRAFT HAVING HORIZONTAL AND 
VERTICAL WINGS AND CRUCIFORM TAIL. 
N. Mastrocola and A. Assadourian. August 19, 
1947. lOOp. diagrs., photos., tab. 
(NACA RM L6J18a) 



HIGH-SPEED STABILITY AND CONTROL CHARAC- 
TERISTICS OF A FIGHTER AIRPLANE MODEL 
WITH A SWEPT-BACK WING AND TAIL. Charles 
P. Morrill, Jr., and Lee E. Boddy. April 14, 1948. 
47p. diagrs., photos. (NACA RM A7K28) 



THE AERODYNAMIC EFFECTS OF ROCKETS AND 
FUEL TANKS MOUNTED UNDER THE SWEPT- 
BACK WING OF AN AIRPLANE MODEL. Lee E. 
Boddy and Charles P. Morrill. Jr. April 23. 1948. 
19p. diagrs. (NACA RM A7J03) 



EFFECTS OF SWEEP ON CONTROLS. John G. 
Lowry, John A. Axelson, and Harold I. Johnson. 
June 3, 1948. 29p. diagrs. (NACA RM L8A28c) 



CONTROL EFFECTIVENESS AND HINGE-MOMENT 
MEASUREMENTS AT A MACH NUMBER OF 1.9 OF 
A NOSE FLAP AND TRAILING-EDGE FLAP ON A 
HIGHLY TAPERED LOW-ASPECT-RATIO WING. 
D. William Conner and Meade H. Mitchell, Jr. 
January 10, 1949. 26p. diagrs., photo. 
(NACA RM L8K17a) 



WIND-TUNNEL INVESTIGATION OF A TAILLESS 
TRIANGULAR-WING FIGHTER AIRCRAFT AT 
MACH NUMBERS FROM 0-5 TO 1.5. Leslie F. 
Lawrence and James L. Summers. June 24, 1949. 
56p. diagrs., photos., tab. (NACA RM A9B16) 



LONGITUDINAL STABILITY AND CONTROL CHAR- 
ACTERISTICS OF A SEMISPAN WIND-TUNNEL 
MODEL OF A TAILLESS AIRPLANE AND A COM- 
PARISON WITH COMPLETE -MODEL WIND-TUNNEL 
TESTS AND SEMISPAN-MODEL WING-FLOW TESTS. 
Kenneth W. Goodson and Thomas J. King, Jr. 
October 10, 1949. 63p. diagrs., photos. 
(NACARM L9C31) 



A STUDY OF SEVERAL FACTORS AFFECTING THE 
STABILITY CONTRIBUTED BY A HORIZONTAL 
TAIL AT VARIOUS VERTICAL POSITIONS ON A 
SWEPTBACK-WING AIRPLANE MODEL. Gerald V. 
Foster and Roland F. Griner. October 28, 1949. 
28p. diagrs., tab. (NACA RM L9H19) 



INVESTIGATION OF A THIN WING OF ASPECT 
RATIO 4 IN THE AMES 12-FOOT PRESSURE WIND 
TUNNEL. V - STATIC LONGITUDINAL STABILITY 
AND CONTROL THROUGHOUT THE SUBSONIC 
SPEED RANGE OF A SEMISPAN MODEL OF A 
SUPERSONIC AIRPLANE. Ben H. Johnson, Jr., 
and Francis W. Rollins. December 8, 1949. 130p. 
diagrs., photos. (NACA RM A9I01) 



AERODYNAMIC CHARACTERISTICS AND FLYING 
QUALITIES OF A TAILLESS TRIANGULAR-WING 
AIRPLANE CONFIGURATION AS OBTAINED FROM 
FLIGHTS OF ROCKET-PROPELLED MODELS AT 
TRANSONIC AND LOW SUPERSONIC SPEEDS. 
Grady L. Mitcham, Joseph E. Stevens, and Harry P. 
Norris. February 9, 1950. 67p. diagrs., photos., 
tabs. (NACA RM L9L07) 



ELEVATOR-STABILIZER EFFECTIVENESS AND 
TRIM OF THE X-l AIRPLANE TO A MACH NUM- 
BER OF 1.06. Hubert M. Drake and John R. Carden. 
November 1, 1950. 12p. diagrs. 
(NACA RM L50G20) 



THE LONGITUDINAL STABILITY, CONTROL EF- 
FECTIVENESS, AND CONTROL HINGE-MOMENT 
CHARACTERISTICS OBTAINED FROM A FLIGHT 
INVESTIGATION OF A CANARD MISSILE CONFIG- 
URATION AT TRANSONIC AND SUPERSONIC 
SPEEDS. Roy J. Niewald and Martin T. Moul. 
November 24, 1950. 43p. diagrs., photos. 
(NACA RM L50I27) 



PRELIMINARY FLIGHT INVESTIGATION OF THE 
MANEUVERING ACCELERATIONS AND BUFFET 
BOUNDARY OF A 35° SWEPT-WING AIRPLANE AT 
HIGH ALTITUDE AND TRANSONIC SPEEDS. 
George A. Rathert, Jr., Howard L. Ziff, and George 
E. Cooper. February 21, 1951. 12p. diagrs., 
photo., tab. (NACA RM A50L04^ 



DYNAMIC STABILITY AND CONTROL CHARACTER- 
ISTICS OF A VERTICALLY RISING AIRPLANE 
MODEL IN HOVERING FLIGHT. William R. Bates, 
Po-vell M. Lovell, Jr., and Charles C. Smith, Jr. 
February 23, 1951. 16p. diagrs., photos., tab. 
(NACA RM L50J16) 



TESTS IN THE AMES 40- BY 80-FOOT WIND TUN- 
NEL OF AN AIRPLANE CONFIGURATION WITH AN 
ASPECT RATIO 2 TRIANGULAR WING AND AN 
ALL-MOVABLE HORIZONTAL TAIL- 
LONGITUDINAL CHARACTERISTICS. David Graham 
and David G. Koenig. April 23, 1951. 35p. diagrs., 
photo., 3 tabs. (NACA RM A51B21) 



AN ANALYSIS OF THE EFFECTS OF AERO- 
ELASTICITY ON STATIC LONGITUDINAL STABIL- 
ITY AND CONTROL OF A SWEPT-BACK-WING 
AIRPLANE. Richard B. Skoog. August 1951. 45p. 
diagrs. (NACA RM A51C19) 



TESTS IN THE AMES 40- BY 80-FOOT WIND TUN- 
NEL OF AN AIRPLANE CONFIGURATION WITH AN 
ASPECT RATIO 4 TRIANGULAR WING AND AN 
ALL-MOVABLE HORIZONTAL TAIL - LONGITUDI- 
NAL CHARACTERISTICS. David Graham and 
David G. Koenig. October 1951. 27p. diagrs., 
photo., 4 tabs. (NACA RM A51H10a) 



DYNAMIC STABILITY AND CONTROL CHARACTER- 
ISTICS OF A DELTA-WING VERTICALLY RISING 
AIRPLANE MODEL IN TAKE-OFFS, LANDINGS, 
AND HOVERING FLIGHT. Powell M. Lovell, Jr., 
William R. Bates and Charles C. Smith, Jr. 
October 1951. 14p. diagrs., photo., tab. (NACA 
RM L51H13a) 



105 



(1) AERODYNAMICS 



THE STATIC LONGITUDINAL CHARACTERISTICS 
AT MACH NUMBERS UP TO 0.95 OF A 
TRIANGULAR-WING CANARD MODEL HAVING A 
TRIANGULAR CONTROL. Jack D. Stephenson and 
Ralph Selan. December 1951. 72p. diagrs., photo. 
{NACA RM A51I07) 



TESTS IN THE AMES 40- BY 80-FOOT WIND TUN- 
NEL OF AN AIRPLANE CONFIGURATION WITH AN 
ASPECT RATIO 2 TRIANGULAR WING AND AN 
ALL-MOVABLE HORIZONTAL TAIL - LATERAL 
CHARACTERISTICS. David Graham and David G. 
Koenig. February 1952. 38p. diagrs., 2 tabs. 
(NACA RM A51L03) 



SOME FACTORS AFFECTING AUTOMATIC CON- 
TROL OF AIRPLANES. Charles W. Mathews. 
February 1952. 15p. diagrs. (NACA RM L52A30) 



USE OF AN AERODYNAMICALLY PULSED ALL- 
MOVABLE HORIZONTAL TAIL TO OBTAIN LONGI- 
TUDINAL CHARACTERISTICS OF ROCKET- 
POWERED MODELS IN FREE FLIGHT AND SOME 
INITIAL RESULTS FROM AN ARR OW -WING- BODY - 
TAIL CONFIGURATION. Warren Gillespie, Jr., and 
Albert E. Dletz. May 1952. 31p. diagrs., photos. 
(NACARM L52C10) 



LONGITUDINAL STABILITY AND CONTROL CHAR- 
ACTERISTICS FROM A FLIGHT INVESTIGATION 
OF A CRUCIFORM CANARD MISSILE CONFIGURA- 
TION HAVING AN EXPOSED WING-CANARD AREA 
RATIO OF 16:1. Martin T. Moul and Andrew R. 
Wineman. June 1952. 32p. diagrs., photos. 
(NACA RM L52D24a) 



EFFECT OF CAMBER AND TWIST ON THE STA- 
BILITY CHARACTERISTICS OF MODELS HAVING A 
45° SWEPT WING AS DETERMINED BY THE FREE- 
FALL METHOD AT TRANSONIC SPEEDS. Maurice 
D. White. August 1952. 35p. diagrs., photos., tab. 
(NACA RMA52F16) 



LONGITUDINAL STABILITY AND CONTROL CHAR- 
ACTERISTICS OF A CANARD MISSILE CONFIGURA- 
TION FOR MACH NUMBERS FROM 1.1 TO 1.93 AS 
DETERMINED FROM FREE-FLIGHT AND WIND- 
TUNNEL INVESTIGATIONS. Howard J. Curfman, 
Jr., and Carl E. Grigsby. August 1952. 28p. 
diagrs., tab. (NACA RM L52F06) 



THE LONGITUDINAL CHARACTERISTICS AT MACH 
NUMBERS UP TO 0.9 OF A WING-FUSELAGE-TAIL 
COMBINATION HAVING A WING WITH 40° OF 
SWEEPBACK AND AN ASPECT RATIO OF 10. 
Bruce E. Tinling. December 1952. 41p. diagrs., 
photo., tab. (NACA RM A52I19) 



LONGITUDINAL -CONTROL EFFECTIVENESS AND 
DOWNWASH CHARACTERISTICS AT TRANSONIC 
SPEEDS OF A 1/ 30-SCALE SEMISPAN MODEL OF 
THE BELL X-5 AIRPLANE AS DETERMINED BY 
THE NACA WING-FLOW METHOD. Norman S. 
Silsby and Garland J. Morris. January 1953. 48p. 
diagrs., photos., 2 tabs. (NACA RM L52K12) 



TESTS IN THE AMES 40- BY 80-FOOT WIND TUN- 
NEL OF AN AIRPLANE MODEL WITH AN ASPECT 
RATIO 4 TRIANGULAR WING AND AN ALL- 
MOVABLE HORIZONTAL TAIL - HIGH-LIFT DE- 
VICES AND LATERAL CONTROLS. Ralph W. 
Franks. February 1953. 45p. diagrs., photo., 2 
tabs. (NACA RM A52K13) 



TESTS IN THE AMES 40- BY 80-FOOT WIND TUN- 
NEL OF TWO AIRPLANE MODELS HAVING AS- 
PECT RATIO 2 TRAPEZOIDAL WINGS OF TAPER 
RATIOS 0.33 AND 0.20. Ralph W. Franks. 
February 1953. 56p. diagrs., photos., 3 tabs. 
(NACARM A52L16) 



TESTS IN THE AMES 40- BY 80-FOOT WIND TUN- 
NEL OF AN AIRPLANE CONFIGURATION WITH AN 
ASPECT RATIO 3 TRIANGULAR WING AND AN 
ALL-MOVABLE HORIZONTAL TAIL - LONGITU- 
DINAL AND LATERAL CHARACTERISTICS. David 
G. Koenig. April 1953. 61p. diagrs., photos., 
4 tabs. (NACA RM A52L15) 



LOW-SPEED INVESTIGATION OF THE AERODY- 
NAMIC, CONTROL, AND HINGE-MOMENT CHAR- 
ACTERISTICS OF TWO TYPES OF CONTROLS ON 
A DELTA-WING-FUSELAGE MODEL WITH AND 
WITHOUT NACELLES. William I. Scallion. May 
1953. 47p. diagrs., photos., tabs. 
NACA RM L53C18) 



THE EFFECTS OF NACELLES AND OF EXTENDED 
SPLIT FLAPS ON THE LONGITUDINAL CHARAC- 
TERISTICS OF A WING-FUSELAGE-TAIL COMBI- 
NATION HAVING A WING WITH 40° OF SWEEP - 
BACK AND AN ASPECT RATIO OF 10. Bruce E. 
Tinling and Armando E. Lopez. June 1953. 47p. 
diagrs., tab. (NACA RM A53D06) 



TESTS IN THE AMES 40- BY 80- FOOT WIND TUN- 
NEL OF AN AIRPLANE CONFIGURATION WITH A 
VARIABLE -INCIDENCE TRIANGULAR WING AND 
AN ALL-MOVABLE HORIZONTAL TAIL. David G. 
Koenig, June 1953. 42p. diagrs., photo., tabs, 
(NACARM A53D21) 



REVIEW AND INVESTIGATION OF UNSATISFAC- 
TORY CONTROL CHARACTERISTICS INVOLVING 
INSTABILITY OF PILOT-AIRPLANE COMBINATION 
AND METHODS FOR PREDICTING THESE DIFFI- 
CULTIES FROM GROUND TESTS. William H. 
Phillips, B. Porter Brown, and James T. Matthews, 
Jr. August 1953. 57p. diagrs., photos. 
(NACARM L53F17a) 



A TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE LONGITUDINAL STABILITY AND CONTROL 
CHARACTERISTICS OF A 0.09-SCALE MODEL OF 
THE BELL X-5 RESEARCH AIRPLANE AND COM- 
PARISON WITH FLIGHT. Ralph P. Bielat and 
George S. Campbell. October 1953. 65p. diagrs., 
photo. (NACA RM L53H18) 



FREE-FLIGHT-TUNNEL INVESTIGATION OF THE 
LOW -SPEED STABILITY AND CONTROL CHARAC- 
TERISTICS OF A CANARD AIRPLANE MODEL. 
Joseph L. Johnson, Jr., and John W. Paulson. 
October 1953. 37p. diagrs., photo., 2 tabs. (NACA 
RM L53I11) 



106 



(1) AERODYNAMICS 



THE RESULTS OF WIND-TUNNEL TESTS AT LOW 
SPEEDS OF A FOUR-ENGINE PROPELLER -DRIVEN 
AIRPLANE CONFIGURATION HAVING A WING WITH 
40° OF SWEEPBACK AND AN ASPECT RATIO OF 
10. George G. Edwards, Donald A. Buell, and 
Jerald K. Dickson. December 1953. 121p. diagrs., 
photo., tabs. (NACA RM A53I28) 



THE EFFECTS OF OPERATING PROPELLERS ON 
THE LONGITUDINAL CHARACTERISTICS AT HIGH 
SUBSONIC SPEEDS OF A FOUR-ENGINE TRACTOR 
AIRPLANE CONFIGURATION HAVING A WING 
WITH 40° OF SWEEPBACK AND AN ASPECT RATIO 
OF 10. Fred B. Sutton and Fred A. Demele. 
January 1954. 106p. diagrs., photo., 11 tabs. 
(NACA RM A53J23) 



HINGE-MOMENT, LIFT, AND PITCHING-MOMENT 
CHARACTERISTICS OF A FLAP-TYPE CONTROL 
SURFACE HAVING VARIOUS HINGE- LINE LOCA- 
TIONS ON A 4-PERCENT-THICK 60° DELTA WING. 
TRANSONIC -BUMP METHOD. Robert F. Thompson. 
March 1954. 73p. diagrs., photo. 
(NACA RM L54B08) 



DYNAMIC STABILITY AND CONTROL CHARACTER- 
ISTICS OF A DUCTED-FAN MODEL IN HOVERING 
FLIGHT. Robert H. Kirby. April 1954. 16p. 
diagrs., photos. (NACA RM L54C18) 



THE EFFECT OF BLUNT-TRAILING-EDGE MODI- 
FICATIONS ON THE HIGH-SPEED STABILITY AND 
CONTROL CHARACTERISTICS OF A SWEPT-WTNG 
FIGHTER AIRPLANE. Melvin Sadoff, Frederick H. 
Matteson, and Rudolph D. Van Dyke, Jr. May 1954. 
55p. diagrs., photos., tab. (NACA RM A54C31) 



ANALYSIS OF WIND-TUNNEL TESTS AT LOW 
SPEEDS OF A FOUR-ENGINE PROPELLER- 
DRIVEN AIRPLANE CONFIGURATION HAVING A 
WING WITH 40° OF SWEEPBACK. George G. 
Edwards and Donald A. Buell. October 1954. 137p 
diagrs., photos., 2 tabs. (NACA RM A54F14) 



A METHOD FOR THE DESIGN OF SWEPTBACK 
WINGS WARPED TO PRODUCE SPECIFIED FLIGHT 
CHARACTERISTICS AT SUPERSONIC SPEEDS. 
Warren A Tucker. 1955. i. 17p. diagrs., tabs. 
(NACA Kept. 1220. Supersedes RM L51F08) 



A FLIGHT EVALUATION OF THE LONGITUDINAL 
STABILITY CHARACTERISTICS ASSOCIATED WITH 
THE PITCH-UP OF A SWEPT -WING AIRPLANE IN 
MANEUVERING FLIGHT AT TRANSONIC SPEEDS. 
Seth B. Anderson and Richard S. Bray. 1955. ii, 
12p. diagrs., photo., tab. (NACA Rept. 1237. 
Supersedes RM A51I12) 



FLIGHT DETERMINATION OF THE LONGITUDINAL 
STABILITY AND CONTROL CHARACTERISTICS OF 
THE BELL X-5 RESEARCH AIRPLANE AT 58.7° 
SWEEPBACK Thomas W. Finch. May 1955. 30p. 
diagrs., photo., tab. (NACA RM H55C07) 



SUMMARY OF RESULTS OF A WIND-TUNNEL 
INVESTIGATION OF NINE RELATED HORIZONTAL 
TAILS. Jules B. Dods. Jr. and Bruce E. Tinling. 
July 1955. 105p. diagrs., 2 tabs. (NACA TN 3497. 
Formerly RM A51G31a) 



HOVERTNG- FLIGHT TESTS OF A MODEL OF A 
TRANSPORT VERTICAL-TAKE-OFF AIRPLANE 
WITH TILTING WING AND PROPELLERS. Powell 
M. Lovell, Jr., and Lysle P. Parlett. March 1956. 
23p diagrs., photo., tab. (NACA TN 3630) 

SOME EFFECTS OF FUSELAGE FLEXIBILITY ON 
LONGITUDINAL STABILITY AND CONTROL. 
Bernard B. Klawans and Harold I. Johnson. April 
1956. 42p. diagrs., tab. (NACA TN 3543) 



ANALYSIS OF A VANE-CONTROLLED GUST- 
ALLEVIATION SYSTEM. Robert W. Boucher and 
Christopher C. Kraft, Jr. April 1956. 45p. 
diagrs., tabs. (NACA TN 3597) 



INVESTIGATION AT ZERO FORWARD SPEED OF A 
LEADING-EDGE SLAT AS A LONGITUDINAL CON- 
TROL DEVICE FOR VERTICALLY RISING AIR- 
PLANES THAT UTILIZE THE REDIRECTED- 
SLIPSTREAM PRINCIPLE. Richard E. Kuhn. 
May 1956. 33p. diagrs., photos. (NACA TN 3692) 



(1. 8. 2. 2) 
LATERAL 

FREE-FLIGHT INVESTIGATION OF CONTROL EF- 
FECTIVENESS OF FULL-SPAN, 0.2-CHORD PLAIN 
AILERONS AT HIGH SUBSONIC, TRANSONIC, AND 
SUPERSONIC SPEEDS TO DETERMINE SOME EF- 
FECTS OF WING SWEEPBACK, TAPER, ASPECT 
RATIO, AND SECTION-THICKNESS RATIO. Carl A. 
Sandahl. August 13, 1947. 16p. diagrs., photos., 
tab. (NACA RM L7F30) 

FLIGHT INVESTIGATION TO DETERMINE THE 
HINGE MOMENTS OF A BEVELED-EDGE AILERON 
ON A 45° SWEPTBACK WING AT TRANSONIC AND 
LOW SUPERSONIC SPEEDS. William N. Gardner 
and Howard J. Curfman, Jr. November 12, 1947. 
20p. diagrs., photos. (NACA RM L7H26) 



THE HIGH-SPEED AERODYNAMIC EFFECTS OF 
MODIFICATIONS TO THE WING AND WING- 
FUSELAGE INTERSECTION OF AN AIRPLANE 
MODEL WITH THE WING SWEPT BACK 35°. Lee 
E. Boddy and Charles P. Morrill, Jr. February 18, 
1948. 34p. diagrs., photos. (NACA RM A7J02) 



HIGH-SPEED STABILITY AND CONTROL CHARAC- 
TERISTICS OF A FIGHTER AIRPLANE MODEL 
WITH A SWEPT -BACK WING AND TAIL. Charles 
P. Morrill, Jr., and Lee E. Boddy. April 14, 1948. 
47p. diagrs., photos. (NACA RM A7K28) 



THE AERODYNAMIC EFFECTS OF ROCKETS AND 
FUEL TANKS MOUNTED UNDER THE SWEPT- 
BACK WING OF AN AIRPLANE MODEL. Lee E. 
Boddy and Charles P. Morrill. Jr. April 23. 1948. 
19p. diagrs. (NACA RM A7J03) 



ADDITIONAL RESULTS IN A FREE -FLIGHT IN- 
VESTIGATION OF CONTROL EFFECTIVENESS OF 
FULL-SPAN, 0.2-CHORD PLAIN AILERONS AT 
HIGH SUBSONIC, TRANSONIC, AND SUPERSONIC 
SPEEDS TO DETERMINE SOME EFFECTS OF WING 
SWEEPBACK, ASPECT RATIO, TAPER, AND SEC- 
TION THICKNESS RATIO. Carl A. Sandahl and 
H. Kurt Strass. April 23, 1948. 31p. diagrs., 
photos. (NACA RM L7L01) 



107 



(1) AERODYNAMICS 



EFFECTS OF SWEEP ON CONTROLS. John G. 
Lowry, John A. Axelson, and Harold I. Johnson. 
June 3, 1948. 29p. diagrs. (NACA RM L8A28c) 



FREE- FLIGHT INVESTIGATION OF THE ROLLING 
EFFECTIVENESS AT HIGH SUBSONIC, TRANSONIC, 
AND SUPERSONIC SPEEDS OF LEADING-EDGE 
AND TRAILING-EDGE AILERONS IN CONJUNCTION 
WITH TAPERED AND UNTAPERED PLAN FORMS. 
H. Kurt Strass. July 23, 1948. 19p. diagrs., 
photos. (NACA RM L8E10) 



FREE- FLIGHT INVESTIGATION OF THE ROLLING 
EFFECTIVENESS OF SEVERAL DELTA WING - 
AILERON CONFIGURATIONS AT TRANSONIC AND 
SUPERSONIC SPEEDS. Carl A. Sandahl. 
August 27, 1948. I9p. diagrs., photos., tab. 
(NACA RM L8D16) 



FREE -FLIGHT INVESTIGATION AT TRANSONIC 
AND SUPERSONIC SPEEDS OF THE ROLLING EF- 
FECTIVENESS OF A THIN, UNSWEPT WING 
HAVING PARTIAL-SPAN AILERONS. Carl A. 
Sandahl. Cctober 22, 1948. 13p. diagrs., photos., 
tab. (NACA RM L8G20a) 



INVESTIGATION OF A THIN WING OF ASPECT 
RATIO 4 IN THE AMES 12-FOOT PRESSURE WIND 
TUNNEL, in - THE EFFECTIVENESS OF A 
CONSTANT-CHORD AILERON. Ben H. Johnson, Jr., 
and Fred A. Demele. November 19, 1948. 26p. 
diagrs., photo. (NACA RM A8I17) 



CONTROL EFFECTIVENESS AND HINGE-MOMENT 
MEASUREMENTS AT A MACH NUMBER OF 1.9 OF 
A NOSE FLAP AND TRAILING-EDGE FLAP ON A 
HIGHLY TAPERED LOW-ASPECT-RATIO WING. 
D. William Conner and Meade H. Mitchell, Jr. 
January 10, 1949. 26p. diagrs., photo. 
(NACA RM L8K17a) 



FREE-FLIGHT INVESTIGATION AT TRANSONIC 
AND SUPERSONIC SPEEDS OF THE ROLLING EF- 
FECTIVENESS OF SEVERAL AILERON CONFIGU- 
RATIONS ON A TAPERED WING HAVING 42.7° 
SWEEPBACK. Carl A. Sandahl. January 11. 1949. 
23p. diagrs., photos., tab, (NACA RM L8K23) 



EXPERIMENTAL AND CALCULATED HINGE 
MOMENTS OF TWO AILERONS ON A 42.7° SWEPT - 
BACK WING AT A MACH NUMBER OF 1.9. 
James C. Swells and Kennith L. Goin. January 19, 
1949. 23p. diagrs., photos., tabs. 
(NACA RML8K24a) 



INVESTIGATION AT A MACH NUMBER OF 1.9 AND 
A REYNOLDS NUMBER OF 2.2 x 10 6 OF SEVERAL 
FLAP-TYPE LATERAL-CONTROL DEVICES ON A 
WING HAVING 42.7° SWEEPBACK OF THE LEAD- 
ING EDGE. Kennith L. Goin. March 11, 1949. 
28p. diagrs.. photos., tabs. (NACA RM L9A18a) 



EFFECTS OF SOME AIRFOIL-SECTION VARIA- 
TIONS ON WING-AILERON ROLLING EFFECTIVE- 
NESS AND DRAG AS DETERMINED IN FREE 
FLIGHT AT TRANSONIC AND SUPERSONIC SPEEDS. 
Carl A. Sandahl, William M. Bland, Jr., and H. Kurt 
Strass. July 22, 1949. 29p. diagrs., photos., tabs. 
(NACA RM L9D12) 



MEASUREMENTS OF AILERON EFFECTIVENESS 
OF THE BELL X-l AIRPLANE AT MACH NUMBERS 
BETWEEN 0.9 AND 1.06. Hubert M. Drake. 
August 4, 1949. 5p. diagrs. (NACA RM L9G19a) 



THE EFFECT OF SPANWISE AILERON LOCATION 
ON THE ROLLING EFFECTIVENESS OF WINGS 
WITH 0° AND 45° SWEEP AT SUBSONIC, TRAN- 
SONIC, AND SUPERSONIC SPEEDS. H. Kurt Strass. 
April 25, 1950. 28p. diagrs., photo. 
(NACA RM L50A27) 



FREE-FLIGHT INVESTIGATION AT TRANSONIC 
AND SUPERSONIC SPEEDS OF THE ROLLING EF- 
FECTIVENESS OF A PARTIAL-SPAN AILERON ON 
AN INVERSELY TAPERED SWEPTBACK WING. 
H. Kurt Strass, E. M. Fields, and E. D. Schult. 
May 1, 1950. 17p. diagrs., photo., tabs. 
(NACA RM L50B08) 



ROLLING EFFECTIVENESS OF A THIN TAPERED 
WING HAVING PARTIAL-SPAN AILERONS AS DE- 
TERMINED BY ROCKET-POWERED TEST 
VEHICLES. Carl A. Sandahl and H. Kurt Strass. 
May 23, 1950. 12p, diagrs., photo. 
(NACARM L50D17) 



WING-DROPPING CHARACTERISTICS OF SOME 
STRAIGHT AND SWEPT WINGS AT TRANSONIC 
SPEEDS AS DETERMINED WITH ROCKET- 
POWERED MODELS. David G. Stone. May 26, 
1950. 12p. diagrs., tab. (NACA KM L50C01) 



EXPERIMENTAL DETERMINATION OF EFFECT 
OF STRUCTURAL RIGIDITY ON ROLLING EFFEC- 
TIVENESS OF SOME STRAIGHT AND SWEPT WINGS 
AT MACH NUMBERS FROM 0.7 TO 1.7. H. Kurt 
Strass, E. M. Fields, and Paul E. Purser. 
October 4, 1950. 4 Op. diagrs.. photo., lab. (NACA 
RM L50G14b) 



DYNAMIC STABILITY AND CONTROL CHARACTER- 
ISTICS OF A VERTICALLY RISING AIRPLANE 
MODEL IN HOVERING FLIGHT. William R. Bates, 
Powell M. Lovell, Jr., and Charles C. Smith, Jr. 
February 23, 1951. 16p. diagrs., photos., tab. 
(NACA RM L50J16) 



WIND-TUNNEL INVESTIGATION AT SUBSONIC AND 
LOW TRANSONIC SPEEDS OF THE EFFECTS OF 
AILERON SPAN AND SPANWISE LOCATION ON THE 
ROLLING CHARACTERISTICS OF A TEST VEHICLE 
WITH THREE UNTAPERED 45° SWEPTBACK 
WINGS. HaroldS. Johnson. April 6, 1951. 26p. 
diagrs., photo., tab. (NACA RM L51B16) 



COMPARISONS OF THE EFFECTIVENESS AND 
HINGE MOMENTS OF ALL-MOVABLE DELTA AND 
FLAP-TYPE CONTROLS ON VARIOUS WINGS. 
David G. Stone. April 19, 1951. 13p. diagrs. 
(NACA RM L51C22) 



SOME EFFECTS OF SPANWISE AILERON LOCA- 
TION AND WING STRUCTURAL RIGIDITY ON THE 
ROLLING EFFECTIVENESS OF 0.3-CHORD FLAP- 
TYPE AILERONS ON A TAPERED WING HAVING 
63° SWEEPBACK AT THE LEADING EDGE AND 
NACA 64A005 AIRFOIL SECTIONS. H. Kurt 
Strass, E. M. Fields, and Eugene D. Schult. 
June 1951. 25p. diagrs., photo., tab. 
(NACA RM L51D18a) 



108 



(1) AERODYNAMICS 



ROLLING EFFECTIVENESS OF ALL-MOVABLE 
WINGS AT SMALL ANGLES OF INCIDENCE AT 
MACH NUMBERS FKOM 0.6 TO 1.6. H. Kurt 
Strassand Edward T. Marley. October 1951. 16p. 
diagrs.. nhoto., tab. (NACA RM L51H03) 



DYNAMIC STABILITY AND CONTROL CHARACTER- 
ISTICS OF A DELTA-WING VERTICALLY RISING 
AIRPLANE MODEL IN TAKE-OFFS, LANDINGS, 
AND HOVERING FLIGHT. Powell M. Lovell, Jr., 
William R. Bates and Charles C. Smith, Jr. 
October 1951. 14p. diagrs., photo., tab. (NACA 
RM L51Hl3a) 



TESTS IN THE AMES 40- BY 80-FOOT WIND TUN- 
NEL OF AN AIRPLANE CONFIGURATION WITH AN 
ASPECT RATIO 2 TRIANGULAR WING AND AN 
ALL-MOVABLE HORIZONTAL TAIL - LATERAL 
CHARACTERISTICS. David Graham and David G. 
Koenig. February 1952. 38p. diagrs., 2 tabs. 
(NACA RM A51L03) 



SOME FACTORS AFFECTING AUTOMATIC CON- 
TROL OF AIRPLANES. Charles W. Mathews. 
February 1952. 15p. diagrs. (NACA KM L52A30) 



LOW-SPEED LATERAL-CONTROL CHARACTER- 
ISTICS OF AN UNSWEPT WING WITH HEXAGONAL 
AIRFOIL SECTIONS AND ASPECT RATIO 2.5 
EQUIPPED WITH SPOILERS AND WITH SHARP- 
AND THICKENED-TRAILING-EDGE FLAP-TYPE 
AILERONS AT A REYNOLDS NUMBER OF 7.6 x 10 b 
James E. Fitzpatrick and Robert L. Woods. April 
1952. 58p. photos., diagrs., tab. 
(NACA RM L52B15) 



FREE-FLIGHT INVESTIGATION AT ZERO LIFT IN 
THE MACH NUMBER RANGE BETWEEN 0.7 AND 
1 4 TO DETERMINE THE EFFECTIVENESS OF AN 
rNSET TAB AS A MEANS OF AERODYNAMICALLY 
RELIEVING AILERON HINGE MOMENTS. William 
M. Bland, Jr., and Edward T. Marley. January 
1953, I9p. diagrs.. photos. (NACA RM L52K07) 

TESTS IN THE AMES 40- BY 80-FOOT WIND TUN- 
NEL OF AN AIRPLANE MODEL WITH AN ASPECT 
RATIO 4 TRIANGULAR WING AND AN ALL- 
MOVABLE HORIZONTAL TAIL - HIGH-LIFT DE- 
VICES AND LATERAL CONTROLS. Ralph W. 
Franks. February 1953. 45p. diagrs. ? photo.. 2 
tabs. (NACA RM A52K13) 



TESTS IN THE AMES 40- BY 80-FOOT WIND TUN- 
NEL OF TWO AIRPLANE MODELS HAVING AS- 
PECT RATIO 2 TRAPEZOIDAL WINGS OF TAPER 
RATIOS 0.33 AND 0.20. Ralph W. Franks. 
February 1953. 56p. diagrs., photos., 3 tabs. 
(NACA RM A52L16) 

FLIGHT MEASUREMENTS OF THE STABILITY 
CHARACTERISTICS OF THE BELL X-5 RESEARCH 
AIRPLANE IN SIDESLIPS AT 59° SWEEPBACK. 
Joan M. Childs. February 1953. 23p. diagrs., 
photos., tab. (NACA RM L52K13b) 



PRELIMINARY RESULTS OF STABILITY AND CON- 
TROL INVESTIGATION OF THE BELL X-5 RE- 
SEARCH AIRPLANE. Thomas W. Finch and Donald 
W. Briggs. February 1953. 35p. diagrs., photos,, 
tabs. (NACARM L52K18b) 



TESTS IN THE AMES 40- BY 80-FOOT WIND TUN- 
NEL OF AN AIRPLANE CONFIGURATION WITH AN 
ASPECT RATIO 3 TRIANGULAR WING AND AN 
ALL-MOVABLE HORIZONTAL TAIL - LONGITU- 
DINAL AND LATERAL CHARACTERISTICS. David 
G Koenig. April 1953. 61p. diagrs., photos., 
4 tabs. (NACA RM A52L15) 



LOW -SPEED AILERON EFFECTIVENESS AS 
DETERMINED BY FORCE TESTS AND VISUAL- 
FLOW OBSERVATIONS ON A 52° SWEPTBACK 
WING WITH AND WITHOUT CHORD-EXTENSIONS. 
Patrick A. Cancro. April 1953. 38p. diagrs., 
photos. (NACA RM L53B26) 



INVESTIGATION OF THE EFFECTS OF WING AND 
TAIL MODIFICATIONS ON THE LOW-SPEED STA- 
BILITY CHARACTERISTICS OF A MODEL HAVING 
A THIN 40° SWEPT WING OF ASPECT RATIO 3.5. 
Joseph Weil, William C. Sleeman, Jr., and Andrew 
L. Byrnes, Jr. April 1953. 95p. diagrs., photos., 
tab. (NACA RM L53C09) 



LOW-SPEED INVESTIGATION OF THE AERODY- 
NAMIC, CONTROL, AND HINGE-MOMENT CHAR- 
ACTERISTICS OF TWO TYPES OF CONTROLS ON 
A DELTA-WING-FUSELAGE MODEL WITH AND 
WITHOUT NACELLES. William I. Scallion. May 
1953. 47p. diagrs., photos., tabs. 
(NACARM L53C18) 



WIND-TUNNEL INVESTIGATION AT HIGH SUB- 
SONIC SPEEDS OF A SPOILER-SLOT-DEFLECTOR 
COMBINATION ON AN NACA 65A006 WING WITH 
QUARTER-CHORD LINE SWEPT BACK 32.6°. 
Raymond D. Vogler. May 1953. 24p. diagrs. 
(NACA RM L53D17) 



THE LATERAL CONTROL CHARACTERISTICS OF 
CONSTANT-PERCENT-CHORD TRAILING- EDGE 
ELEVONS ON A POINTED WING OF ASPECT RATIO 
2 AT MACH NUMBERS UP TO 0.95. Verlin D. Reed 
and Donald W. Smith. August 1953. 105p. diagrs., 
photo., tabs. (NACA RM A53F03) 



LOW-SPEED WIND-TUNNEL INVESTIGATION OF A 
JET CONTROL ON A 35° SWEPT WING. John G. 
Lowry and Thomas R. Turner. October 1953. 9p. 
diagrs. (NACA RM L53I09a) 

SOME EFFECTS OF AEROELASTICITY AND 
SWEEP3ACK ON THE ROLLING EFFECTIVENESS 
AND DRAG OF A 1/11-SCALE MODEL OF THE 
BELL X-5 AIRPLANE WING AT MACH NUMBERS 
FROM 0.6 TO 1.5. Roland D. English. November 
1953. 21p. diagrs.. photos. (NACA RM L53H8b) 



HINGE-MOMENT. LIFT, AND PITCHING-MOMENT 
CHARACTERISTICS OF A FLAP-TYPE CONTROL 
SURFACE HAVING VARIOUS HINGE-LINE LOCA- 
TIONS ON A 4-PERCENT-THICK 60° DELTA WING. 
TRANSONIC-BUMP METHOD. Robert F. Thompson. 
March 1954. 73p. diagrs., photo. 
(NACA RM L54B08) 



DYNAMIC STABILITY AND CONTROL CHARACTER- 
ISTICS OF A DUCTED-FAN MODEL IN HOVERING 
FLIGHT. Robert H. Kirby. April 1954. 16p. 
diagrs., photos. (NACA RM L54C18) 



109 



(1) AERODYNAMICS 



THE EFFECT OF BLUNT-TRAILING-EDGE MODI- 
FICATIONS ON THE HIGH-SPEED STABILITY AND 
CONTROL CHARACTERISTICS OF A SWEPT-WING 
FIGHTER AIRPLANE. Melvin Sadoff, Frederick H. 
Matteson, and Rudolph D. Van Dyke, Jr. May 1954. 
55p. diagrs., photos., tab. (NACA RM A54C31) 



EFFECT AT TRANSONIC SPEEDS OF INBOARD 
SPOILERS ON THE STATIC LONGITUDINAL STA- 
BILITY CHARACTERISTICS OF A 45° SWEPTBACK 
WING-BODY COMBINATION HAVING A LEADING- 
EDGE CHORD-EXTENSION. James H. Henderson. 
June 1954. 24p. diagrs., photo. 
(NACA RM L54D13) 



COMPARISON BETWEEN THEORETICAL AND EX- 
PERIMENTAL RATES OF ROLL OF TWO MODELS 
WITH FLEXIBLE RECTANGULAR WINGS AT SU- 
PERSONIC SPEEDS. John M. Hedgepeth and 
Robert J. KeLl. August 1954. 21p. diagrs., photo., 
tabs. (NACA RM L54F23) 



CHARTS FOR ESTIMATING TAIL-ROTOR CONTRI- 
BUTION TO HELICOPTER DIRECTIONAL STABIL- 
ITY AND CONTROL IN LOW-SPEED FLIGHT. 
Kenneth B. Amer and Alfred Gessow. 1955. ii, 
22p. diagrs., photo., tabs. (NACA Rept. 1216. 
Supersedes TN 3156) 



THF EFFFCTTVKNESS OF WTNG VORTEX GENERA- 
TORS IN IMPROVING THE MANEUVERING CHARAC- 
TERISTICS OF A SWEPT-WING AIRPLANE AT 

TRANSONIC SPEEDS. Norman M. McFadden, 
George A. Rathert, Jr., and Richard S. Bray. 
September 1955. 43p. diagrs., photos., tab. 
(NACA TN 3523. Supersedes RM A51J18) 



THEORETICAL ANALYSIS OF LINKED LEADING- 
EDGE AND TRAILING-EDGE FLAP-TYPE CON- 
TROLS AT SUPERSONIC SPEEDS. E. Carson 
Yates, Jr. March 1956. 40p. diagrs., tab. 
(NACA TN 3617) 



HOVERING-FLIGHT TESTS OF A MODEL OF A 
TRANSPORT VERTICAL-TAKE-OFF AIRPLANE 
WITH TILTING WING AND PROPELLERS. Powell 
M. Lovell, Jr., and Lysle P. Parlett. March 1956. 
23p diagrs., photo., tab. (NACA TN 3630) 



ANALYTICAL STUDY OF MODIFICATIONS TO THE 
AUTOPILOT OF A FIGHTER AIRPLANE IN ORDER 
TO REDUCE THE RESPONSE TO SIDE GUSTS. 
Charles W. Mathews and James J. Adams. March 
1956. 35p. diagrs., tabs. (NACA TN 3635) 



FLIGHT INVESTIGATION OF THE EFFECTIVENESS 
OF AN AUTOMATIC AILERON TRIM CONTROL 
DEVICE FOR PERSONAL AIRPLANES. William H. 
Phillips, Helmut A. Kuehnel and James B. Whitten. * 
April 1956. 42p. diagrs., photos., tab. 
(NACA TN 3637) 



INVESTIGATION OF LATERAL CONTROL NEAR 
THE STALL. FLIGHT TESTS WITH HIGH-WING 
AND LOW-WING MONOPLANES OF VARIOUS CON- 
FIGURATIONS. FredE. Weick and H. Norman 
Abramson, Agricultural and Mechanical College of 
Texas. June 1956. 34p. diagrs., photos., tabs. 
(NACA TN 3676) 



INVESTIGATION OF LATERAL CONTROL NEAR 
THE STALL. ANALYSIS FOR REQUIRED LONGI- 
TUDINAL TRIM CHARACTERISTICS AND DISCUS- 
SION OF DESIGN VARIABLES. FredE. Weick and 
H. Norman Abramson, Agricultural and Mechanical 
College of Texas. June 1956. 91p. diagrs., tabs. 
(NACA TN 3677) 



(1. 8. 2. 3) 
DIRECTIONAL 

EFFECTS OF SWEEP ON CONTROLS. John G. 
Lowry, John A. Axelson, and Harold I. Johnson. 
June 3, 1948. 29p. diagrs. (NACA RM L8A28c) 

AERODYNAMIC STUDY OF A WING-FUSELAGE 
COMBINATION EMPLOYING A WING SWEPT BACK 
63°. - AERODYNAMIC CHARACTERISTICS IN 
SIDESLIP OF A LARGE-SCALE MODEL HAVING A 
63° SWEPT-BACK VERTICAL TAIL. Gerald M. 
McCormack. October 7, 1949. 26p. diagrs., 
photos. (NACA RM A9F14) 

FLIGHT DETERMINATION OF THE EFFECTS OF 
RUDDER-PEDAL-FORCE CHARACTERISTICS ON 
THE AIMING ERROR IN AZIMUTH OF A CONVEN- 
TIONAL FIGHTER AIRPLANE. Lee Winograd and 
Rudolph D, Van Dyke, Jr. July 5, 1950. 32p. 
diagrs., photos., tab. (NACA RM A50D06) 

EFFECT OF THE PROXIMITY OF THE GROUND ON 
THE STABILITY AND CONTROL CHARACTERIS- 
TICS OF A VERTICALLY RISING AIRPLANE MODEL 
IN THE HOVERING CONDITION. Charles C. Smith, 
Jr., Powell M. Lovell, Jr., and William R. Bates. 
September 1951. 16p. diagrs., tab. (NACA 
RML51G05) 

TESTS IN THE AMES 40- BY 80-FOOT WIND TUN- 
NEL OF AN AIRPLANE CONFIGURATION WITH AN 
ASPECT RATIO 2 TRIANGULAR WING AND AN 
ALL-MOVABLE HORIZONTAL TAIL - LATERAL 
CHARACTERISTICS. David Graham and David G. 
Koenig. February 1952. 38p. diagrs., 2 tabs. 
(NACA RM A51L03) 



SOME FACTORS AFFECTING AUTOMATIC CON- 
TROL OF AIRPLANES. Charles W. Mathews. 
February 1952. 15p. diagrs. (NACA RM L52A30) 

TESTS IN THE AMES 40- BY 80-FOOT WIND TUN- 
NEL OF AN AIRPLANE MODEL WITH AN ASPECT 
RATIO 4 TRIANGULAR WING AND AN ALL- 
MOVABLE HORIZONTAL TAIL - HIGH-LIFT DE- 
VICES AND LATERAL CONTROLS. Ralph W. 
Franks. February 1953. 45p. diagrs., photo., 2 
tabs. (NACA RM A52K13) 

TESTS IN THE AMES 40- BY 80-FOOT WIND TUN- 
NEL OF TWO AIRPLANE MODELS HAVING AS- 
PECT RATIO 2 TRAPEZOIDAL WINGS OF TAPER 
RATIOS 0.33 AND 0.20. Ralph W. Franks. 
February 1953. 56p. diagrs., photos., 3 tabs. 
(NACA RM A52L16) 

FLIGHT MEASUREMENTS OF THE STABILITY 
CHARACTERISTICS OF THE BELL X-5 RESEARCH 
AIRPLANE IN SIDESLIPS AT 59° SWEEPBACK. 
JoanM. Childs. February 1953. 23p. diagrs., 
photos., tab. (NACA RM L52K13b) 



110 



(1) AERODYNAMICS 



TESTS IN THE AMES 40- BY 80-FOOT WIND TUN- 
NEL OF AN AIRPLANE CONFIGURATION WITH AN 
ASPECT RATIO 3 TRIANGULAR WING AND AN 
ALL-MOVABLE HORIZONTAL TAIL - LONGITU- 
DINAL AND LATERAL CHARACTERISTICS. David 
G. Koenig. April 1953. 61p. diagrs., photos., 
4 tabs. (NACA RM A52L15) 



FREE-FLIGHT -TUNNEL INVESTIGATION OF THE 
LOW-SPEED STABILITY AND CONTROL CHARAC- 
TERISTICS OF A CANARD AIRPLANE MODEL. 
Joseph L. Johnson, Jr., and John W. Paulson. 
October 1953. 37p. diagrs., photo., 2 tabs. (NACA 
RM L53I11) 



A STUDY OF THE CHARACTERISTICS OF HUMAN- 
PILOT CONTROL RESPONSE TO SIMULATED AIR- 
CRAFT LATERAL MOTIONS. Donald C. Cheatham. 
1954. ii, 14p. diagrs., photos., tab. {NACA 
Rept, 1197. Formerly RM L52C17) 



SUMMARY OF RESULTS OF A WIND-TUNNEL 
INVESTIGATION OF NINE RELATED HORIZONTAL 
TAILS. Jules B. Dods, Jr. and Bruce E. Tinling. 
July 1955. 105p. diagrs., 2 tabs. (NACA TN 3497. 
Formerly RM A51G31a) 



HOVERING-FLIGHT TESTS OF A MODEL OF A 
TRANSPORT VERTICAL-TAKE-OFF AIRPLANE 
WITH TILTING WING AND PROPELLERS. Powell 
M. Lovell, Jr., and Lysle P. Parlett. March 1956. 
23p diagrs., photo., tab. (NACA TN 3630) 



ANALYTICAL STUDY OF MODIFICATIONS TO THE 
AUTOPILOT OF A FIGHTER AIRPLANE IN ORDER 
TO REDUCE THE RESPONSE TO SIDE GUSTS. 
Charles W. Mathews and James J. Adams. March 
1956. 35p. diagrs., tabs. (NACA TN 3635) 



(1.8. 2.4) 
AIR BRAKES 

HIGH-SPEED STABILITY AND CONTROL CHARAC- 
TERISTICS OF A FIGHTER AIRPLANE MODEL 
WITH A SWEPT-BACK WING AND TAIL. Charles 
P. Morrill, Jr., and Lee E. Boddy. April 14, 1948. 
47p. diagrs., photos. (NACA RM A7K28) 

EFFECT AT TRANSONIC SPEEDS OF INBOARD 
SPOILERS ON THE STATIC LONGITUDINAL STA- 
BILITY CHARACTERISTICS OF A 45° SWEPTBACK 
WING-BODY COMBINATION HAVING A LEADING- 
EDGE CHORD-EXTENSION. James H. Henderson. 
June 1954. 24p. diagrs., photo. 
(NACA RM L54D13) 

PRELIMINARY PERFORMANCE DATA OF SEVERAL 
TAIL-PIPE-CASCADE-TYPE MODEL THRUST 
REVERSERS. James G. Henzel, Jr. and Jack G. 
McArdle. August 1955. 48p. diagrs., photos., tab. 
(NACA RM E55F09) 

(1. 8. 2. 5) 
HINGE MOMENTS 

FLIGHT INVESTIGATION TO DETERMINE THE 
HINGE MOMENTS OF A BEVELED-EDGE AILERON 
ON A 45° SWEPTBACK* WING AT TRANSONIC AND 
LOW SUPERSONIC SPEEDS. William N. Gardner 
and Howard J. Curfman, Jr. November 12, 1947. 
20p. diagrs., photos. (NACA RM L7H26) 



THE HIGH-SPEED AERODYNAMIC EFFECTS OF 
MODIFICATIONS TO THE WING AND WING- 
FUSELAGE INTERSECTION OF AN AIRPLANE 
MODEL WITH THE WING SWEPT BACK 35°. Lee 
E. Boddy and Charles P. Morrill, Jr. February 18, 
1948. 34p. diagrs., photos. (NACA RM A7J02) 

HIGH-SPEED STABILITY AND CONTROL CHARAC- 
TERISTICS OF A FIGHTER AIRPLANE MODEL 
WITH A SWEPT-BACK WING AND TAIL. Charles 
P. Morrill, Jr., and Lee E. Boddy. April 14, 1948. 
47p. diagrs., photos. (NACA RM A7K28) 

EFFECTS OF SWEEP ON CONTROLS. John G. 
Lowry, John A. Axelson, and Harold I. Johnson. 
June 3, 1948. 29p. diagrs. (NACA RM L8A28c) 

CONTROL EFFECTIVENESS AND HINGE-MOMENT 
MEASUREMENTS AT A MACH NUMBER OF 1.9 OF 
A NOSE FLAP AND TRAILING-EDGE FLAP ON A 
HIGHLY TAPERED LOW-ASPECT-RATIO WING. 
D. William Conner and Meado H. Mitchell, Jr. 
January 10, 1949. 26p. diagrs., photo. 
(NACA RM LBK17a) 

HINGE-MOMENT MEASUREMENTS OF A WING 
WITH LEADING-EDGE AND TRAILING-EDGE 
FLAPS AT A MACH NUMBER OF 1.93. William B. 
Boatright and Robert W. Rainey. January 14, 1949. 
12p. diagrs., tab. (NACA RM L8K12a) 



EXPERIMENTAL AND CALCULATED HINGE 
MOMENTS OF TWO AILERONS ON A 42.70 SWEPT- 
BACK WING AT A MACH NUMBER OF 1.9. 
James C. Sivells and Kennith L. Goin. January 19, 
1949. 23p. diagrs., photos., tabs. 
(NACA RML8K24a) 



AERODYNAMIC STUDY OF A WING-FUSELAGE 
COMBINATION EMPLOYING A WING SWEPT BACK 
63°. - AERODYNAMIC CHARACTERISTICS IN 
SIDESLIP OF A LARGE-SCALE MODEL HAVING A 
63° SWEPT-BACK VERTICAL TAIL. Gerald M. 
McCormack. October 7, 1949. 26p. diagrs., 
photos. (NACA RM A9F14) 



AERODYNAMIC CHARACTERISTICS AND FLYING 
QUALITIES OF A TAILLESS TRIANGULAR-WING 
AIRPLANE CONFIGURATION AS OBTAINED FROM 
FLIGHTS OF ROCKET-PROPELLED MODELS AT 
TRANSONIC AND LOW SUPERSONIC SPEEDS. 
Grady L. Mitcham, Joseph E. Stevens, and Harry P. 
Norris. February 9, 1950. 67p. diagrs., photos., 
tabs. (NACA RM L9L07) 

THE TRANSONIC CHARACTERISTICS OF A LOW- 
ASPECT-RATIO TRIANGULAR WING WITH A 
CONSTANT-CHORD FLAP AS DETERMINED BY 
WING-FLOW TESTS, INCLUDING CORRELATION 
WITH LARGE-SCALE TESTS. George A. Rathert, 
Jr., L. Stewart Rolls, and Carl M. Hanson. 
July 18, 1950. 39p. diagrs., photo. 
(NACA RM A50E10) 



THE LONGITUDINAL STABILITY, CONTROL EF- 
FECTIVENESS, AND CONTROL HINGE-MOMENT 
CHARACTERISTICS OBTAINED FROM A FLIGHT 
INVESTIGATION OF A CANARD MISSILE CONFIG- 
URATION AT TRANSONIC AND SUPERSONIC 
SPEEDS. Roy J. Niewald and Martin T. Moul. 
November 24, 1950. 43p. diagrs., photos. 
(NACA RM L50I27) 



Ill 



(1) AERODYNAMICS 



COMPARISONS OF THE EFFECTIVENESS AND 
HINGE MOMENTS OF ALL-MOVABLE DELTA AND 
FLAP-TYPE CONTROLS ON VARIOUS WINGS. 
David G. Stone. April 19, 1951. 13p. diagrs. 
(NACA RM L51C22) 



LOW-SPEED LATERAL-CONTROL CHARACTER- 
ISTICS OF AN UNSWEPT WING WITH HEXAGONAL 
AIRFOIL SECTIONS AND ASPECT RATIO 2.5 
EQUIPPED WITH SPOILERS AND WITH SHARP- 
AND THICKENED-TRAILING-EDGE FLAP-TYPE 
AILERONS AT A REYNOLDS NUMBER OF 7.6 x 10 6 
James E. Fitzpatrick and Robert L. Woods. April 
1952. 58p. photos., diagrs., tab. 
{NACA RM L52B15) 

PRELIMINARY DATA AT A MACH NUMBER OF 2.40 
OF THE CHARACTERISTICS OF FLAP-TYPE CON- 
TROLS EQUIPPED WITH PLAIN OVERHANG BAL- 
ANCES. James N. Mueller and K. R. Czarnecki. 
September 1952. 43p. diagrs., photos. 
(NACA RM L52F10) 



FREE-FLIGHT INVESTIGATION AT ZERO LIFT IN 
THE MACH NUMBER RANGE BETWEEN 0.7 AND 
1.4 TO DETERMINE THE EFFECTIVENESS OF AN 
INSET TAB AS A MEANS OF AERODYNAMICALLY 
RELIEVING AILERON HINGE MOMENTS. William 
M. Bland, Jr., and Edward T, Marley. January 
1953. I9p, diagrs., photos. (NACA RM L52K07) 



LOW-SPEED INVESTIGATION OF THE AERODY- 
NAMIC, CONTROL, AND HINGE-MOMENT CHAR- 
ACTERISTICS OF TWO TYPES OF CONTROLS ON 
A DELTA-WING-FUSELAGE MODEL WITH AND 
WITHOUT NACELLES. William I. Scallion. May 
1953. 47p. diagrs., photos., tabs. 
(NACA RM L53C18) 



AILERON AND ELEVATOR HINGE MOMENTS OF 
THE BELL X-l AIRPLANE MEASURED IN TRAN- 
SONIC FLIGHT. Hubert M. Drake and John B. 
McKay. June 1953. 27p. diagrs. 
(NACA RM L53E04) 



THE LATERAL CONTROL CHARACTERISTICS OF 
CONSTANT-PERCENT-CHORD TRAILING-EDGE 
ELEVONS ON A POINTED WING OF ASPECT RATIO 
2 AT MACH NUMBERS UP TO 0.95. Verlin D. Reed 
and Donald W. Smith. August 1953. 105p. diagrs., 
photo., tabs. (NACA RM A53F03) 



A TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE LONGITUDINAL STABILITY AND CONTROL 
CHARACTERISTICS OF A 0.09-SCALE MODEL OF 
THE BELL X-5 RESEARCH AIRPLANE AND COM- 
PARISON WITH FLIGHT. Ralph P. Bielat and 
GeorgeS. Campbell. October 1953. 65p. diagrs., 
photo. (NACA RM L53H18) 

HINGE-MOMENT, LIFT, AND PITCHING-MOMENT 
CHARACTERISTICS OF A FLAP-TYPE CONTROL 
SURFACE HAVING VARIOUS HINGE- LINE LOCA- 
TIONS ON A 4-PERCENT-THICK 60° DELTA WING. 
TRANSONIC -BUMP METHOD. Robert F, Thompson. 
March 1954. 73p. diagrs., photo. 
(NACA RM L54B08) 

LARGE-SCALE LOW -SPEED WIND-TUNNEL TESTS 
OF A MODEL HAVING A 60° DELTA HORIZONTAL 
CANARD CONTROL SURFACE AND WING TO OB- 
TAIN STATIC-LONGITUDINAL-STABILITY AND 
CANARD-SURFACE HINGE-MOMENT DATA. 
Dale L. Burrows. June 1954. 21p. diagrs. 
(NACA RM L54D16a) 



SUMMARY OF RESULTS OF A WIND-TUNNEL 
INVESTIGATION OF NINE RELATED HORIZONTAL 
TAILS. Jules B. Dods, Jr. and Bruce E. Tinling. 
July 1955. 105p. diagrs., 2 tabs. (NACA TN 3497. 
Formerly RM A51G31a) 

THEORETICAL ANALYSIS OF LINKED LEADING- 
EDGE AND TRAILING-EDGE FLAP-TYPE CON- 
TROLS AT SUPERSONIC SPEEDS. E. Carson 
Yates, Jr. March 1956. 40p. diagrs., tab. 
(NACA TN 3617) 



(1.8. 2.6) 

AUTOMATIC 



ROCKET-POWERED FLIGHT TEST OF A ROLL- 
STABILIZED SUPERSONIC MISSILE CONFIGURA- 
TION. Robert A. Gardiner and Jacob Zarovsky, 
January 12, 1950. 32p. diagrs., photos., tab. 
(NACA RM L9K01a) 



FLIGHT INVESTIGATION OF A ROLL-STABILIZED 
MISSILE CONFIGURATION AT VARYING ANGLES 
OF ATTACK AT MACH NUMBERS BETWEEN 0.8 
AND 1.79. Jacob Zarorsky and Robert A. Gardiner, 
March 6, 1951. 38p. diagrs., photos., tab. 
(NACARM L50H21* 



SOME FACTORS AFFECTING AUTOMATIC CON- 
TROL OF AIRPLANES. Charles W. Mathews. 
February 1952. 15p. diagrs. (NACA RM L52A30) 



THEORETICAL INVESTIGATION OF SOME DISCON- 
TINUOUS YAW DAMPERS. William H. Phillips and 
'Helmut A. Kuehnel. April 1954. 39p. diagrs. 
I .'NACARM L54B24a) 



THEORETICAL AND ANALOG STUDIES OF THE 
EFFECTS OF NONLINEAR STABILITY DERIVA- 
TIVES ON THE LONGITUDINAL MOTIONS OF AN 
AIRCRAFT IN RESPONSE TO STEP CONTROL 
DEFLECTIONS AND TO THE INFLUENCE OF PRO- 
PORTIONAL AUTOMATIC CONTROL. Howard J. 
Curfman, Jr. 1955. 11, 21p. diagrs. (NACA 
Rept. 1241. Supersedes RM L50L11) 



FROM LINEAR MECHANICS TO NONLINEAR 
MECHANICS. (De la mecanique lineaire a la 
mecanique non lineaire). Julien Loeb. October 

1955. 18p. diagrs. (NACA TM 1396. Trans, 
from Annales des Telecommunications, v.5, no. 2, 
Feb., 1950, p. 65-71) 

LABORATORY INVESTIGATION OF AN AUTOPILOT 
UTILIZING A MECHANICAL LINKAGE WITH A 
DEAD SPOT TO OBTAIN AN EFFECTIVE RATE 
SIGNAL. Ernest C. Seaberg. December 1955. 27p. 
diagrs., photos., tab. (NACA TN 3602. Supersedes 
RM L9F15a) 

ANALYTICAL STUDY OF MODIFICATIONS TO THE 
AUTOPILOT OF A FIGHTER AIRPLANE IN ORDER 
TO REDUCE THE RESPONSE TO SIDE GUSTS. 
Charles W. Mathews and James J. Adams. March 

1956. 35p. diagrs., tabs. (NACA TN 3635) 



INITIAL RESULTS OF A FLIGHT INVESTIGATION 
OF A GUST -ALLEVIATION SYSTEM. Christopher 
C. Kraft, Jr. April 1956. 19p. diagrs., photos., 
tabs. (NACA TN 3612) 



112 



(1) AERODYNAMICS 



(1.8.3) 
SPINNING 



FREE-SPINNING-TUNNEL INVESTIGATION OF 
GYROSCOPIC EFFECTS OF JET-ENGINE R6TAT- 
ING PARTS (OR OF ROTATING PROPELLERS) ON 
SPIN AND SPIN RECOVERY. James S. Bowman, Jr. 
August 1955. 21p. diagrs., photo., 2 tabs., 6 charts. 
(NACA TN 3480) 

PILOT'S LOSS OF ORIENTATION IN INVERTED 
SPINS. Stanley H. Scher. October 1955. lOp. 
diagrs., photos. (NACA TN 3531) 



ANALYSIS OF A SPIN AND RECOVERY FROM 
TIME HISTORIES OF ATTITUDES AND VELOCI- 
TIES AS DETERMINED FOR A DYNAMIC MODEL 
OF A CONTEMPORARY FIGHTER AIRPLANE IN 
THE FREE-SPINNING TUNNEL. Stanley H. Scher. 
April 1956. 54p, diagrs., photos., tabs. 
(NACA TN3611) 



(1.8.4) 
STALLING 



EFFECTS OF HIGH-LIFT AND STALL-CONTROL 
DEVICES, FUSELAGE, AND HORIZONTAL TAIL ON 
A WING SWEPT BACK 42° AT THE LEADING EDGE 
AND HAVING SYMMETRICAL CIRCULAR-ARC AIR- 
FOIL SECTIONS AT A REYNOLDS NUMBER OF 
6.9 x 10 6 . Robert L. Woods and Stanley H. 
Spooner. April 20, 1949. 42p. diagrs., photos., 
tabs. (NACA RM L9B11) 

TABULATED PRESSURE COEFFICIENTS AND 
AERODYNAMIC CHARACTERISTICS MEASURED 
ON THE WING OF THE BELL X-l AIRPLANE IN 

AN UNACCELERATED STALL AND IN PULL-UPS 
AT MACH NUMBERS OF 0.74, 0.75, 0.94, AND 
0.97. Lawrence A. Smith. June 19, 1951. 49p. 
diagrs., photo., tabs. (NACA RM L51B23) 

THE USE OF LEADING-EDGE AREA SUCTION TO 
INCREASE THE MAXIMUM LIFT COEFFICIENT OF 
A 35° SWEPT-BACK WING. Curt A. Holzhauserand 
Robert K. Martin. September 1952. 37p. diagrs., 
photo., 3 tabs. (NACA RM A52G17) 

A FLIGHT INVESTIGATION OF THE EFFECT OF 
LEADING-EDGE CAMBER ON THE AERODYNAMIC 
CHARACTERISTICS OF A SWEPT -WING AIRPLANE. 
Seth B. Anderson, Frederick H. Matteson, and 
Rudolph D. Van Dyke, Jr. February 1953. 23p. 
diagrs., photos., tab. (NACA RM A52L16a) 

PRELIMINARY RESULTS OF STABILITY AND CON- 
TROL INVESTIGATION OF THE BELL X-5 RE- 
SEARCH AIRPLANE. Thomas W. Finch and Donald 
W. Briggs. February 1953. 35p. diagrs., photos., 
tabs. (NACA RM L52K18b) 

WIND-TUNNEL INVESTIGATION OF STALL CON- 
TROL BY SUCTION THROUGH A POROUS LEADING 
EDGE ON A 37° SWEPTBACK WING OF ASPECT 
RATIO 6 AT REYNOLDS NUMBERS FROM 2.50xl0 6 
to 8.10 x 10 6 . Robert R. Graham and William A. 
Jacques. March 1953. 67p. diagrs., photo., 2 tabs. 
(NACA RM L52L05) 



THE EFFECTS OF FENCES ON THE HIGH-SPEED 
LONGITUDINAL STABILITY OF A SWEPT-WING 
AIRPLANE. RichardS. Bray. August 1953. 37p. 
diagrs., photos., tabs. (NACA RM A53F23) 

MEASUREMENT AND ANALYSIS OF WING AND 
TAIL BUFFETING LOADS ON A FIGHTER AIR- 
PLANE. WilberB. Huston and T. H. Skopinski. 
1955. i, 27p. diagrs., photo., tabs. (NACA Rept. 
1219. Supersedes TN 3080) 



FLIGHT TESTS OF LEADING-EDGE AREA SUCTION 
ON A FIGHTER-TYPE AIRPLANE WITH A 35° 
SWEPTBACK WING. RichardS. Bray and Robert C. 
Innis. June 1955. 30p. diagrs., photos., tab. 
(NACA RM A55C07) 

EFFECTS OF SWEEP ON THE MAXIMUM-LIFT 
CHARACTERISTICS OF FOUR ASPECT -RATIO-4 
WINGS AT TRANSONIC SPEEDS. Thomas R. Turner. 
July 1955. 25p. diagrs. (NACA TN 3468. Formerly 
RM L50H11) 



THE EFFECT OF REYNOLDS NUMBER ON THE 
STALLING CHARACTERISTICS AND PRESSURE 
DISTRIBUTIONS OF FOUR MODERATELY THIN 
AIRFOIL SECTIONS. George B. McCullough. 
November 1955. 24p. diagrs., tabs. 
(NACA TN 3524) 



PRELIMINARY STUDY OF SOME FACTORS WHICH 
AFFECT THE STALL-FLUTTER CHARACTER- 
ISTICS OF THIN WINGS. A. Gerald Rainey. March 
1956. 33p. diagrs., photo., tab. (NACA TN 3622. 
Supersedes RM L52D08) 

INVESTIGATION OF LATERAL CONTROL NEAR 
THE STALL. FLIGHT TESTS WITH HIGH-WING 
AND LOW -WING MONOPLANES OF VARIOUS CON- 
FIGURATIONS. FredE. Weick and H. Norman 
Abramson, Agricultural and Mechanical College of 
Texas. June 1956. 34p. diagrs., photos., tabs. 
(NACA TN 3676) 



INVESTIGATION OF LATERAL CONTROL NEAR 
THE STALL. ANALYSIS FOR REQUIRED LONGI- 
TUDINAL TRIM CHARACTERISTICS AND DISCUS- 
SION OF DESIGN VARIABLES. Fred E. Weick and 
H. Norman Abramson, Agricultural and Mechanical 
College of Texas. June 1956. 91p. diagrs., tabs. 
(NACA TN 3677) 



(1.8.5) 
FLYING QUALITIES 



PRELIMINARY RESULTS OF NACA TRANSONIC 
FLIGHTS OF THE XS-1 AIRPLANE WITH 10- 

PERCENT-THICK WING AND 8-PERCENT-THICK 
HORIZONTAL TAIL. Hubert M. Drake, Harold R. 
Goodman, and Herbert H. Hoover. October 13, 1948. 
18p. diagrs., photos. (NACA RM L8I29) 



PRELIMINARY THEORETICAL AND FLIGHT IN- 
VESTIGATION OF THE LATERAL OSCILLATION 
OF THE X-l AIRPLANE. Hubert M. Drake and 
Helen L. Wall. July 19, 1949. 24p. diagrs., photo., 
tab. (NACA RM L9F07) 



113 



(1) AERODYNAMICS 



AERODYNAMIC CHARACTERISTICS AND FLYING 
QUALITIES OF A TAILLESS TRIANGULAR- WING 
AIRPLANE CONFIGURATION AS OBTAINED FROM 
FLIGHTS OF ROCKET-PROPELLED MODELS AT 
TRANSONIC AND LOW SUPERSONIC SPEEDS. 
Grady L. Mitcham, Joseph E. Stevens, and Harry P. 
Norris. February 9, 1950. 67p. diagrs., photos., 
tabs. (NACA RM L9L07) 



FLIGHT MEASUREMENTS OF THE STABILITY 
CHARACTERISTICS OF THE BELL X-5 RESEARCH 
AIRPLANE IN SIDESLIPS AT 59° SWEEPBACK. 
Joan M. Childs. February 1953. 23p. diagrs., 
photos., tab. (NACA RM L52K13b) 



PRELIMINARY RESULTS OF STABILITY AND CON- 
TROL INVESTIGATION OF THE BELL X-5 RE- 
SEARCH AIRPLANE. Thomas W. Finch and Donald 
W. Briggs. February 1953. 35p. diagrs., photos., 
tabs. (NACA RM L52K18b) 



FLIGHT DETERMINATION OF THE STATIC LONGI- 
TUDINAL STABILITY BOUNDARIES OF THE BELL 
X-5 RESEARCH AIRPLANE WITH 59° SWEEPBACK. 
Thomas W. Finch and Joseph A. Walker. February 
1953. 51p. diagrs., photo., tab. 
(NACA RM L53A09b) 



STUDIES OF THE SPEED STABILITY OF A TAN- 
DEM HELICOPTER IN FORWARD FLIGHT. Robert 
J. Tapscott and Kenneth B. Amer. August 1053. 
35p. diagrs., photos., tab. (NACA RM L53Fl5a) 



REVIEW AND INVESTIGATION OF UNSATISFAC- 
TORY CONTROL CHARACTERISTICS INVOLVING 
INSTABILITY OF PILOT-AIRPLANE COMBINATION 
AND METHODS FOR PREDICTING THESE DIFFI- 
CULTIES FROM GROUND TESTS. William H. 
Phillips, B. Porter Brown, and James T. Matthews, 
Jr. August 1953. 57p. diagrs., photos. 
(NACA RML53F17a) 



SOME DESIGN CONSIDERATIONS PERTINENT TO 
THE ROUGH-AIR BEHAVIOR OF AIRPLANES AT 
LOW ALTITUDE. Philip Donely and Clarence L. 
Gillis. November 1953. 21p. diagrs., tabs. 
(NACA RM L53J01b) 



A STUDY OF THE PROBLEM OF DESIGNING AIR- 
PLANES WITH SATISFACTORY INHERENT DAMP- 
ING OF THE DUTCH ROLL OSCILLATION. John P. 
Campbell and Marion O. McKinney, Jr. 1954. ii, 
18p. diagrs., tabs. (NACA Rept. 1199. Super- 
sedes TN 3035) 

METHOD FOR STUDYING HELICOPTER LONGITU- 
DINAL MANEUVER STABILITY. Kenneth B. Amer. 
1954, ii, 17p. diagrs., photos., tabs. 
(NACA Rept. 1200. Supersedes TN 3022) 



STUDIES OF THE LATERAL -DIRECTIONAL FLY- 
ING QUALITIES OF A TANDEM HELICOPTER IN 
FORWARD FLIGHT. Kenneth B. Amer and Robert 
J. Tapscott. 1954. ii, 15p. diagrs., photos., tab. 
(NACA Rept. 1207. Supersedes TN 2984) 

FLIGHT TESTS OF A 0.4 -SCALE MODEL OF A 
STAND-ON TYPE OF VERTICALLY RISING AIR- 
CRAFT. Marion O. McKinney and Lysie P. Parlett. 
March 1954. 23p. diagrs., photos. (NACA 
RM L54B16b) 



FLIGHT INVESTIGATION OF THE EFFECTS OF A 
PARTIAL-SPAN LEADING-EDGE CHORD EXTEN- 
SION OF THE AERODYNAMIC CHARACTERISTICS 
OF A 35° SWEPT -WING FIGHTER AIRPLANE, 
Frederick H, Matteson and Rudolph D. Van Dyke, Jr. 
April 1954. 34p. diagrs., photos., tabs. 
(NACA RM A54B26) 



METHODS FOR OBTAINING DESIRED HELICOPTER 
STABILITY CHARACTERISTICS. F. B. Gustafson 
and Robert J. Tapscott. August 1954. 12p. tabs. 
(NACA RM L54F30) 

METHODS OF PREDICTING HELICOPTER STABIL- 
ITY. Robert J. Tapscott and F. B. Gustafson. 
November 1954. 15p. diagrs. (NACA RM L54G05) 

CHARTS FOR ESTIMATING TAIL-ROTOR CONTRI- 
BUTION TO HELICOPTER DIRECTIONAL STABIL- 
ITY AND CONTROL IN LOW-SPEED FLIGHT. 
Kenneth B. Amer and Alfred Gessow. 1955. ii, 
22p. diagrs., photo., tabs. (NACA Rept. 1216. 
Supersedes TN 3156) 

FLIGHT DETERMINATION OF THE LONGITUDINAL 
STABILITY AND CONTROL CHARACTERISTICS OF 
THE BELL X-5 RESEARCH AIRPLANE AT 58.7° 
SWEEPBACK. Thomas W. Finch. May 1955. 30p. 
diagrs., photo., tab. (NACA RM H55C07) 

A COMPARISON OF THE MEASURED AND PRE- 
DICTED LATERAL OSCILLATORY CHARACTERIS- 
TICS OF A 35° SWEPT -WING FIGHTER AIRPLANE. 
Walter E. McNeili and ueorge E. Cooper. August 
1955. 22p. diagrs., photo., 3 tabs. (NACA 
TN 3521. Formerly RM A51C28) 



NOTE ON HOVERING TURNS WITH TANDEM 
HELICOPTERS. John P. Reeder and Robert J. 
Tapscott. September 1955. 5p. photo. (NACA 
RM L55G21) 

HELICOPTER INSTRUMENT FLIGHT AND PRECI- 
SION MANEUVERS AS AFFECTED BY CHANGES IN 
DAMPING IN ROLL, PITCH, AND YAW. James B. 
Whitten, John P. Reeder, and Aimer D. Crim. 
November 1955. 14p. diagrs., photos. 
(NACA TN 3537) 

HOVERING- FLIGHT TESTS OF A MODEL OF A 
TRANSPORT VERTICAL-TAKE-OFF AIRPLANE 
WITH TILTING WING AND PROPELLERS, Powell 
M. Lovell, Jr., and Lysle P. Parlett. March 1956. 
23p diagrs., photo., tab. (NACA TN 3630) 



(1.8.6) 
MASS AND GYROSCOPIC 
PROBLEMS 

PRELIMINARY THEORETICAL AND FLIGHT IN- 
VESTIGATION OF THE LATERAL OSCILLATION 
OF THE X-l AIRPLANE. Hubert M. Drake and 
Helen L. Wall, July 19, 1949. 24p. diagrs., photo., 
tab. (NACA RM L9F07) 



A STUDY OF THE PROBLEM OF DESIGNING AIR- 
PLANES WITH SATISFACTORY INHERENT DAMP- 
ING OF THE DUTCH ROLL OSCILLATION. John P. 
Campbell and Marion O. McKinney, Jr. 1954. ii, 
18p. diagrs., tabs. (NACA Rept. 1199. Super- 
sedes TN 3035) 



114 



(1) AERODYNAMICS 



FREE-SPINNING-TUNNEL INVESTIGATION OF 
GYROSCOPIC EFFECTS OF JET-ENGINE ROTAT- 
ING PARTS (OR OF ROTATING PROPELLERS) ON 
SPIN AND SPIN RECOVERY. James S. Bowman, Jr. 
August 1955. 21p. diagrs., photo., 2 tabs., 6 charts. 
(NACA TN 3480) 



FLIGHT MEASUREMENTS OF THE DYNAMIC 
LATERAL AND LONGITUDINAL STABILITY OF 
THE BELL X-5 RESEARCH AIRPLANE AT 58.7° 
SWEEPBACK. Edward N. Videan. October 1955. 
68p. diagrs., photo., tabs. (NACA RM H55H10) 



(1.8.8) 
AUTOMATIC STABILIZATION 



ROCKET-POWERED FLIGHT TEST OF A ROLL- 
STABILIZED SUPERSONIC MISSILE CONFIGURA- 
TION. Robert A. Gardiner and Jacob Zarovsky. 
January 12, 1950. 32p. diagrs., photos., tab. 
(NACA RM L9K01a) 



FLIGHT INVESTIGATION OF A ROLL-STABILIZED 
MISSILE CONFIGURATION AT VARYING ANGLES 
OF ATTACK AT MACH NUMBERS BETWEEN 0.8 
AND 1.79. Jacob Zarovsky and Robert A. Gardiner. 
March 6, 1951. 38p. diagrs., photos., tab. 
(NACARM L50H21) 

PRELIMINARY THEORETICAL INVESTIGATION OF 
SEVERAL METHODS FOR STABILIZING THE 
LATERAL MOTION OF A HIGH-SPEED FIGHTER 
AIRPLANE TOWED BY A SINGLE CABLE. 
Albert A. Schy and Carroll H. Woodling. March 
1953. 46p. diagrs., 2 tabs. (NACA RM L52L24) 



THEORETICAL INVESTIGATION OF SOME DISCON- 
TINUOUS YAW DAMPERS. William H. Phillips and 
Helmut A. Kuehnel. April 1954. 39p. diagrs. 
(NACA RM L54B24a) 



THEORETICAL AND ANALOG STUDIES OF THE 
EFFECTS OF NONLINEAR STABILITY DERIVA- 
TIVES ON THE LONGITUDINAL MOTIONS OF AN 
AIRCRAFT IN RESPONSE TO STEP CONTROL 
DEFLECTIONS AND TO THE INFLUENCE OF PRO- 
PORTIONAL AUTOMATIC CONTROL. Howard J. 
Curfman, Jr. 1955. ii, 21p. diagrs. (NACA 
Rept. 1241. Supersedes RM L50L11) 



FROM LINEAR MECHANICS TO NONLINEAR 
MECHANICS. (De la mecanique lineaire a la 
mecanique non lineaire). Julien Loeb. October 
1955. 18p. diagrs. (NACA TM 1396. Trans, 
from Annales des Telecommunications, v. 5, no. 2, 
Feb., 1950, p. 65-71) 



THEORETICAL STUDY OF THE LATERAL FRE- 
QUENCY RESPONSE TO GUSTS OF A FIGHTER AIR- 
PLANE, BOTH WITH CONTROLS FDCED AND WITH 
SEVERAL TYPES OF AUTOPILOTS. James J. 
Adams and Charles W. Mathews. March 1956. 46p. 
diagrs., tabs. (NACA TN 3603) 



HOVERING-FLIGHT TESTS OF A MODEL OF A 
TRANSPORT VERTICAL-TAKE-OFF AIRPLANE 
WITH TILTING WING AND PROPELLERS. Powell 
M. Lovell, Jr., and Lysle P. Parlett. March 1956. 
23p diagrs., photo., tab. (NACA TN 3630) 

ANALYTICAL STUDY OF MODIFICATIONS TO THE 
AUTOPILOT OF A FIGHTER AIRPLANE IN ORDER 
TO REDUCE THE RESPONSE TO SIDE GUSTS. 
Charles W. Mathews and James J. Adams. March 
1956. 35p. diagrs., tabs. (NACA TN 3635) 



ANALYSIS OF A VANE -CONTROLLED GUST- 
ALLEVIATION SYSTEM. Robert W. Boucher and 
Christopher C. Kraft, Jr. April 1956. 45p. 
diagrs., tabs. (NACA TN 3597) 

FLIGHT INVESTIGATION OF THE EFF ECTIVENESS 
OF AN AUTOMATIC AILERON TRIM CONTROL 
DEVICE FOR PERSONAL AIRPLANES. William H. 
Phillips, Helmut A. Kuehnel and James B. Whitten. 
April 1956. 42p. diagrs., photos., tab. 
(NACA TN3637) 



115 



(1) AERODYNAMICS 



(1.9) 
Aeroelasticity 



ROLLING EFFECTIVENESS OF A THIN TAPERED 
WING HAVING PARTIAL-SPAN AILERONS AS DE- 
TERMINED BY ROCKET-POWERED TEST 
VEHICLES. Carl A. Sandahl and H. Kurt Strass. 
May 23, 1950. 12p. diagrs., photo. 
(NACA RM L50D17) 



EXPERIMENTAL DETERMINATION OF EFFECT 
OF STRUCTURAL RIGIDITY ON ROLLING EFFEC- 
TIVENESS OF SOME STRAIGHT AND SWEPT WINGS 
AT MACH NUMBERS FROM 0.7 TO 1.7. H. Kurt 
Strass, E. M. Fields, and Paul E. Purser. 
October 4, 1950. 40p. diagrs., photo., tab. (NACA 
RM L50G14b) 



SOME EFFECTS OF SPANWISE AILERON LOCA- 
TION AND WING STRUCTURAL RIGIDITY ON THE 
ROLLING EFFECTIVENESS OF 0.3-CHORD FLAP- 
TYPE AILERONS ON A TAPERED WING HAVING 
63° SWEEPBACK AT THE LEADING EDGE AND 
NACA 64A005 AIRFOIL SECTIONS. H. Kurt 
Strass, E. M. Fields, and Eugene D. Schult. 
June I95i, 25p. diagrs., photo., tab. 
(NACA RM L51D18a) 



RECENT EXPERIMENTAL FLUTTER STUDIES. 
Arthur A. Regier and Dennis J. Martin. June 12, 
1951. 18p. diagrs. (NACA RM L51F11) 



AN ANALYSIS OF THE EFFECTS OF AERO- 
ELASTICITY ON STATIC LONGITUDINAL STABIL- 
ITY AND CONTROL OF A SWEPT-BACK-WING 
AIRPLANE. Richard B. Skoog. August 1951. 45p. 
diagrs. (NACA RM A51C19) 



WIND-TUNNEL INVESTIGATION OF THE AERODY- 
NAMIC CHARACTERISTICS IN PITCH OF WING- 
FUSELAGE COMBINATIONS AT HIGH SUBSONIC 
SPEEDS. ASPECT-RATIO SERIES. Richard E. 
Kuhn and James W. Wiggins. April 1952. 42p. 
diagrs., photos., tab. (NACA RM L52A29) 



WIND-TUNNEL INVESTIGATION OF THE AERO- 
DYNAMIC CHARACTERISTICS IN PITCH OF WING- 
FUSELAGE COMBINATIONS AT HIGH -SUBSONIC 
SPEEDS. SWEEP SERIES. James W. Wiggins and 
Richard E. Kuhn. July 1952. 41p. diagrs., photos. 
(NACA RM L52D18) 



RESULTS OF TWO EXPERIMENTS ON FLUTTER 
OF HIGH-ASPECT-RATIO SWEPT WINGS IN THE 
TRANSONIC SPEED RANGE. W. T. Lauten, Jr., 
and Burke R. O'Kelly. July 1952, 22p. diagrs., 
photos., tabs. (NACA RM L52D24b) 



LONGITUDINAL STABILITY, TRIM, AND DRAG 
CHARACTERISTICS OF A ROCKET-PROPELLED 
MODEL OF AN AIRPLANE CONFIGURATION HAV- 
ING A 45° SWEPTBACK WING AND AN UNSWEPT 
HORIZONTAL TAIL. James H. Parks and Alan B. 
Kehlet. August 1952. 29p. diagrs., photos., tab. 
(NACA RM L52F05) 



SOME EXPERIMENTAL STUDIES OF PANEL 
FLUTTER AT MACH NUMBER 1.3. Maurice A. 
Sylvester and John E. Baker. December 1952. 
25p. diagrs., photos., tab. (NACA RM L52I16) 



WIND-TUNNEL INVESTIGATION OF THE STATIC 
LATERAL STABILITY CHARACTERISTICS OF 
WING-FUSELAGE COMBINATIONS AT HIGH SUB- 
SONIC SPEEDS. ASPECT-RATIO SERIES. Paul G. 
Fournier and Andrew L. Byrnes, Jr. February 1953. 
26p. diagrs., photos. (NACA RM L52L18) 



WIND-TUNNEL INVESTIGATION OF THE AERODY- 
NAMIC CHARACTERISTICS IN PITCH OF WING- 
FUSELAGE COMBINATIONS AT HIGH SUBSONIC 
S^fcaus. TAPER- KA TIG SERIES. Thomas J. 
King, Jr. and Thomas B. Pasteur, Jr. June 1953. 
37p. diagrs., photos., tab. (NACA RM L53E20) 



A COLLECTION OF DATA FOR ZERO-LIFT DAMP- 
ING IN ROLL OF WING-BODY COMBINATIONS AS 
DETERMINED WITH ROCKET-POWERED MODELS 
EQUIPPED WITH ROLL-TORQUE NOZZLES. 
David G. Stone. July 1953. 23p. diagrs., tab. 
(NACA RML53E26) 



SOME EFFECTS OF AEROELASTICITY AND 
SWEEPBACK ON THE ROLLING EFFECTIVENESS 
AND DRAG OF A 1/H-SCALE MODEL OF THE 
BELL X-5 AIRPLANE WING AT MACH NUMBERS 
FROM 0.6 TO 1.5. Roland D. English. November 
1953. 21p. diagrs., photos. (NACA RM L53I18b) 



EXPERIMENTAL INVESTIGATION OF THE OSCIL- 
LATING FORCES AND MOMENTS ON A TWO- 
DIMENSIONAL WING EQUIPPED WITH AN OSCIL- 
LATING CIRCULAR-ARC SPOILER. Sherman A. 
Clevenson and John E. Tomassoni. January 1954. 
20p. diagrs., photos. (NACA RM L53K18) 



COMPARISON BETWEEN THEORETICAL AND EX- 
PERIMENTAL RATES OF ROLL OF TWO MODELS 
WITH FLEXIBLE RECTANGULAR WINGS AT SU- 
PERSONIC SPEEDS. John M. Hedgepeth and 
Robert J. Kell. August 1954. 21p. diagrs., photo 
tabs. (NACA RM L54F23) 



THEORETICAL INVESTIGATION OF FLUTTER OF 
TWO-DIMENSIONAL FLAT PANELS WITH ONE 
SURFACE EXPOSED TO SUPERSONIC POTENTIAL 
FLOW. Herbert C. Nelson and Herbert J. 
Cunningham. July 1955. 60p. diagrs., tab. (NACA 
TN 3465) 



116 



(1) AERODYNAMICS 



SOME EFFECTS OF SYSTEM NONLINEARITIES IN 
THE PROBLEM OF AIRCRAFT FLUTTER. 
Donald S. Woolston, Harry L. Runyan, and Thomas 
A. Byrdsong. October 1955. 20p. diagrs., tabs. 
(NACA TN 3539) 



SOME EFFECTS OF FUSELAGE FLEXIBILITY ON 
LONGITUDINAL STABILITY AND CONTROL. 
Bernard B. Klawans and Harold I. Johnson. April 
1956. 42p. diagrs., tab. (NACA TN 3543) 



ON PANEL FLUTTER AND DIVERGENCE OF INFI- 
NITELY LONG UNSTIFFENED AND RING- 
STIFFENED THIN-WALLED CIRCULAR CYLINDERS. 
Robert W. Leonard and John M. Hedgepeth. April 
1956. 52p. diagrs. (NACA TN 3638) 



EXPERIMENTAL MEASUREMENTS OF FORCES 
AND MOMENTS ON A TWO-DIMENSIONAL OSCIL- 
LATING WING AT SUBSONIC SPEEDS. Sherman A. 
Clevenson and Edward Widmayer, Jr. June 1956. 
28p. diagrs., tab. (NACA TN 3686. Supersedes 
RM L9K28a) 



(2) 



(2) 
HYDRODYNAMICS 



117 



(2) HYDRODYNAMICS 



(2.1) 
Theory 



ESTIMATION OF WATER LANDING LOADS ON 
HYDRO-SKI-EQUIPPED AIRCRAFT. Emanuel 
Schnitzel*. July 1953. 14p. diagrs. 
(NACA RM L53D29) 



A THEORETICAL AND EXPERIMENTAL INVESTI- 
GATION OF THE LIFT AND DRAG CHARACTERIS- 
TICS OF HYDROFOILS AT SUBCRITICAL AND 
SUPERCRITICAL SPEEDS. Kenneth L. Wadlin, 
Charles L. Shuford, Jr., and John R. McGehee. 
1955. ii, 22p. diagrs., photos., tab. (NACA Rept. 
1232. Supersedes RM L52D23a) 



APPROXIMATE HYDRODYNAMIC DESIGN OF A 
FINITE SPAN HYDROFOIL. (Priblizhennyi 
gidrodinamicheskii raschet podvodnogo kryla 
konechnogo razmakha). A. N. Vladimirov. June 
1955. 58p. diagrs., 5 tabs. (NACA TM 1341. 
Trans, from Central Aero-Hydrodynamical Institute, 
Rept. 311, 1937). 



HYDRODYNAMIC PRESSURE DISTRIBUTIONS OB- 
TAINED DURING A PLANING INVESTIGATION OF 
FIVE RELATED PRISMATIC SURFACES. Walter J. 
Kapryan and George M. Boyd, Jr. September 1955. 
82p. diagrs., photos., 5 tabs. (NACA TN 3477) 



HYDRODYNAMIC IMPACT LOADS IN SMOOTH 
WATER FOR A PRISMATIC FLOAT HAVING AN 
ANGLE OF DEAD RISE OF 10°. Philip M. Edge, 
Jr. January 1956. 20p. diagrs., tab. 
(NACA TN 3608) 



AN EXPERIMENTAL INVESTIGATION OF THE 
SCALE RELATIONS FOR THE IMPINGING WATER 
SPRAY GENERATED BY A PLANING SURFACE. 
Ellis E. McBride. February 1956. 42p. diagrs., 
photos., tab, (NACA TN 3615) 



EFFECT OF CARRIAGE MASS UPON THE LOADS 
AND MOTIONS OF A PRISMATIC BODY DURING 
HYDRODYNAMIC IMPACT. Melvin F. Markey. 
March 1956. 45p. diagrs. (NACA TN 3619) 



118 



(2) HYDRODYNAMICS 



(2.2) 
General Arrangement Studies 



NACA MODEL INVESTIGATIONS OF SEAPLANES 
IN WAVES. John B. Parkinson. (Presented at 
Conference on Ships and Waves, Stevens Institute of 
Technology, Cct. 25-27, 1954) July 1955. 28p. 
diagrs., photos. (NACA TN 3419) 



HYDRODYNAMIC PRESSURE DISTRIBUTIONS OB- 
TAINED DURING A PLANING INVESTIGATION OF 
FIVE RELATED PRISMATIC SURFACES. Walter J. 
Kapryan and George M. Boyd, Jr. September 1955. 
82p. diagrs., photos., Stabs. (NACA TN 3477) 



AN EXPERIMENTAL INVESTIGATION OF THE 
SCALE RELATIONS FOR THE IMPINGING WATER 
SPRAY GENERATED BY A PLANING SURFACE. 
Ellis E. McBride. February 1956. 42p. diagrs., 
photos., tab. (NACA TN 3615) 



EFFECT OF SHALLOW WATER ON THE HYDRO- 
DYNAMIC CHARACTERISTICS OF A FLAT-BOTTOM 
PLANING SURFACE. Kenneth W. Christopher. 
April 1956. 36p. diagrs., photos., tab. 
(NACA TN 3642) 



119 



(2) HYDRODYNAMICS 



(2.3) 
Seaplane Hull Variables 



PLANING CHARACTERISTICS OF THREE SUR- 
FACES REPRESENTATIVE OF HYDRO-SKI FORMS. 
Kenneth L. Wadlin and John R. McGehee. March 29, 
1949. 94p. diagrs., photos., tab. 
(NACA RM L9C03) 



(2.3.1) 
LENGTH -BEAM RATIO 

WATER LANDING INVESTIGATION OF A HYDRO- 
SKI MODEL AT BEAM LOADINGS OF 18.9 AND 4.4. 
Sidney A. Batter son. September 1951. 54p. 
diagrs., photos., tab. (NACA RM L51F27) 



ESTIMATION OF WATER LANDING LOADS ON 
HYDRO-SKI-EQUIPPED AIRCRAFT. Emanuel 
Schnitzer. July 1953. 14p. diagrs. 
(NACA RML53D29) 



NACA MODEL INVESTIGATIONS OF SEAPLANES 

IN WAVES. John B. Parkinson. (Presented at 
Conference on Ships and Waves, Stevens Institute of 
Technology, Cct. 25-27, 1954) July 1955. 28p. 
diagrs., photos. (NACA TN 3419) 



IIYDRODYNAMIC PRESSURE DISTRIBUTIONS OB- 
TAINED DURING A PLANING INVESTIGATION OF 
FIVE RELATED PRISMATIC SURFACES. Walter J. 
Kapryan and George M. Boyd, Jr. September 1955. 
82p. diagrs., photos., 5 tabs. (NACA TN 3477) 



EFFECT OF CARRIAGE MASS UPON THE LOADS 
AND MOTIONS OF A PRISMATIC BODY DURING 
HYDRODYNAM1C IMPACT. Melvin F. Markey. 
March 1956. 45p. diagrs. (NACA TN 3619) 



EFFECT OF SHALLOW WATER ON THE HYDRO- 
DYNAMIC CHARACTERISTICS OF A FLAT-BOTTOM 
PLANING SURFACE. Kenneth W. Christopher. 
April 1956. 36p. diagrs., photos., tab. 
(NACA TN 3642) 



(2.3.2) 
DEAD RISE 



PLANING CHARACTERISTICS OF THREE SUR- 
FACES REPRESENTATIVE OF HYDRO-SKI FORMS. 
Kenneth L. Wadlin and John R. McGehee. March 29, 
1949. 94p. diagrs., photos., tab. 
(NACA RM L9C03) 



WATER LANDING INVESTIGATION OF A HYDRO- 
SKI MODEL AT BEAM LOADINGS OF 18.9 AND 4.4. 
Sidney A. Batter son. September 1951. 54p. 
diagrs., photos., tab. (NACA RM L51F27) 



ESTIMATION OF WATER LANDING LOADS ON 
HYDRO-SKI-EQUIPPED AIRCRAFT. Emanuel 
Schnitzer. July 1953. 14p. diagrs. 
(NACA RM L53D29) 



NACA MODEL INVESTIGATIONS OF SEAPLANES 
IN WAVES. John B. Parkinson. (Presented at 
Conference on Ships and Waves, Stevens Institute of 
Technology. Cct. 25-27, 1954) July 1955. 28p. 
diagrs., photos. (NACA TN 3419) 



HYDRODYNAMIC PRESSURE DISTRIBUTIONS OB- 
TAINED DURING A PLANING INVESTIGATION OF 
FIVE RELATED PRISMATIC SURFACES. Walter J. 
Kapryan and George M. Boyd, Jr. September 1955. 
82p. diagrs., photos., 5 tabs. (NACA TN 3477) 



HYDRODYNAMIC IMPACT LOADS IN SMOOTH 
WATER FOR A PRISMATIC FLOAT HAVING AN 
ANGLE OF DEAD RISE OF 10°. Philip M. Edge. 
Jr. January 1956. 20p. diagrs., tab. 
(NACA TN 3608) 



EFFECT OF CARRIAGE MASS UPON THE LOADS 
AND MOTIONS OF A PRISMATIC BODY DURING 
HYDRODYNAMIC IMPACT. Melvin F. Markey. 
March 1956. 45p. diagrs. (NACA TN 3619) 



(2.3.5) 
FOREBODY SHAPE 



NACA MODEL INVESTIGATIONS OF SEAPLANES 

IN WAVES. John B. Parkinson. (Presented at 
Conference on Ships and Waves, Stevens Institute of 
Technology, Cct. 25-27, 1954) July 1955. 28p. 
diagrs., photos. (NACA TN 3419) 



HYDRODYNAMIC IMPACT LOADS IN SMOOTH 
WATER FOR A PRISMATIC FLOAT HAVING AN 
ANGLE OF DEAD RISE OF 10°. Philip M. Edge, 
Jr. January 1956. 20p. diagrs., tab. 
(NACA TN 3608) 



(2.3.6) 
CHINES 



HYDRODYNAMIC PRESSURE DISTRIBUTIONS OB- 
TAINED DURING A PLANING INVESTIGATION OF 
FIVE RELATED PRISMATIC SURFACES. Walter J. 
Kapryan and George M. Boyd, Jr. September 1955. 
82p. diagrs., photos., 5 tabs. (NACA TN 3477) 



120 



(2) HYDRODYNAMICS 



(2.6) 
Planing Surfaces 



PLANING CHARACTERISTICS OF THREE SUR- 
FACES REPRESENTATIVE OF HYDRO-SKI FORMS. 
Kenneth L. Wadlin and John R. McGehee. March 29, 
1949. 94p. diagrs., photos., tab. 
(NACA RM L9C03) 



WATER LANDING INVESTIGATION OF A HYDRO - 
SKI MODEL AT BEAM LOADINGS OF 18.9 AND 4.4. 
Sidney A. Batter son. September 1951. 54p. 
diagrs., photos., tab. (NACA RM L51F271 



AN INVESTIGATION OF A METHOD FOR OBTAIN- 
ING HYDRODYNAMIC DATA AT VERY HIGH 
SPEEDS WITH A FREE WATER JET. Bernard 
Weinflash and John R. McGehee. June 1954. 28p. 
diagrs., photos., tabs. (NACA RM L54D23) 



HYDRODYNAMIC PRESSURE DISTRIBUTIONS OB- 
TAINED DURING A PLANING INVESTIGATION OF 
FIVE RELATED PRISMATIC SURFACES. Walter J. 
Kapryan and George M. Boyd, Jr. September 1955. 
82p. diagrs., photos., 5 tabs. (NACA TN 3477) 



AN EXPERIMENTAL INVESTIGATION OF THE 
SCALE RELATIONS FOR THE IMPINGING WATER 
SPRAY GENERATED BY A PLANING SURFACE. 
Ellis E. McBride. February 1956. 42p. diagrs., 
photos., tab. (NACA TN 3615) 

EFFECT OF SHALLOW WATER ON THE HYDRO- 
DYNAMIC CHARACTERISTICS OF A FLAT-BOTTOM 
PLANING SURFACE. Kenneth W. Christopher. 
April 1956. 36p. diagrs., photos., tab. 
(NACA TN 3642) 



PRELIMINARY INVESTIGATION OF SELF- 
EXCITED VIBRATIONS OF SINGLE PLANING 
SURFACES. Elmo J. Mottard. June 1956. 19p. 
diagrs., photos., tab. (NACA TN 3698. Supersedes 
RM L55J27) 



121 



(2) HYDRODYNAMICS 



(2.7) 
Hydrofoils 



EFFECTS OF A SWEPTBACK HYDROFOIL ON THE 
FORCE AND LONGITUDINAL STABILITY CHARAC- 
TERISTICS OF A TYPICAL HIGH-SPEED AIR- 
PLANE. Raymond B. Wood. December 2, 1948. 
19p. diagrs., photo., tabs. (NACA RM L8I30a) 

ESTIMATION OF WATER LANDING LOADS ON 
HYDRO-SKI-EQUIPPED AIRCRAFT. Emanuel 
Schnitzer. July 1953. 14p. diagrs 
(NACA RM L53D29) 



A THEORETICAL AND EXPERIMENTAL INVESTI- 
GATION OF THE LIFT AND DRAG CHARACTERIS- 
TICS OF HYDROFOILS AT SUBCRITICAL AND 
SUPERCRITICAL SPEEDS. Kenneth L. Wadlin, 
Charles L. Shuford, Jr., and John R. McGehee. 
1955. ii, 22p. diagrs., photos., tab. (NACA Rept. 
1232. Supersedes RM L52D23a) 



APPROXIMATE HYDRODYNAMIC DESIGN OF A 
FINITE SPAN HYDROFOIL. (Priblizhennyi 
gidrodinamicheskii raschet podvodnogo kryla 
konechnogo razmakha). A. N. Vladimirov. June 
1955. 58p. diagrs., Stabs. (NACA TM 1341, 
Trans, from Central Aero-Hydrodynamicallnstitute, 
Rept. 311, 1937). 



EFFECT OF CARRIAGE MASS UPON THE LOADS 
AND MOTIONS OF A PRISMATIC BODY DURING 
HYDRODYNAMIC IMPACT. Melvin F. Markey 
March 1956. 45p. diagrs. (NACA TN 3619) 



122 



(2) HYDRODYNAMICS 



(2.8) 
Surface Craft 



HYDRODYNAMIC IMPACT LOADS IN SMOOTH 
WATER FOR A PRISMATIC FLOAT HAVING AN 
ANGLE OF DEAD RISE OF 10°. Philip M. Edge, 
Jr. January 1956. 20p. diagrs., tab. 
{NACA TN 3608) 



123 
(2) HYDRODYNAMICS 



(2.10) 
Stability and Control 



PRELIMINARY INVESTIGATION OF SELF- 
EXCITED VIBRATIONS OF SINGLE PLANING 
SURFACES. Elmo J. Mottard. June 1956. 19p. 
diagrs., photos., tab. (NACA TN 3698. Supersedes 
RM L55J27) 



(3) 



(3) 
PROPULSION 



125 



(3) PROPULSION 



(3) 
PROPULSION 



SUMMARY EVALUATION OF TOOTHED-NOZZLE 
ATTACHMENTS AS A JET -NOISE -SUPPRESSION 
DEVICE. Warren J. North. July 1955. 19p. 
diagrs., photo. (NACA TN 3516) 

EFFECT OF EXHAUST-NOZZLE EJECTORS ON 
TURBOJET NOISE GENERATION. Warren J. North 
and Willard D. Coles. October 1955. 26p. diagrs., 
photo. (NACA TN 3573) 



EFFECT OF CLIMB TECHNIQUE ON JET- 
TRANSPORT NOISE. Warren J. North. January 
1956. 19p. diagrs. (NACA TN 3582) 



126 



(3) PROPULSION 



(3.1) 
Complete Systems 



EXPERIMENTAL INVESTIGATION OF THRUST 
AUGMENTATION OF 4000- POUND-THRUST 
CENTRIFUGAL-FLOW-TYPE TURBOJET ENGINE 
BY BLEEDOFF. William L. Jones and Louis J. 
Bogdan. July 3, 1950. 30p. diagrs., photo. 
(NACARME50D17) 



(3.U) 
RECIPROCATING ENGINES 



METEOROLOGICAL PROBLEMS ASSOCIATED 
WITH COMMERCIAL TUBOJET -AIRCRAFT OPER- 
ATION. A working group of the NACA Subcommittee 
on Meteorological Problems. June 1955. 46p. 
(NACA RM 54L29) 



FULL-SCALE PERFORMANCE STUDY OF A PRO- 
TOTYPE CRASH-FIRE PROTECTION SYSTEM FOR 
RECIPROCATING-ENGINE-POWERED AIRPLANES. 
Dugald O. Black and Jacob C. Moser. November 
1955. 36p. diagrs., photos. (NACA RM E55B11) 



(3.1.3) 
TURBOJET ENGINES 



EXPERIMENTAL INVESTIGATION OF THRUST 
AUGMENTATION OF 4000-POUND-THRUST AXIAL- 
FLOW -TYPE TURBOJET ENGINE BY INTERSTAGE 
INJECTION OF WATER- ALCOHOL MIXTURES IN 
COMPRESSOR. John H. Povolny, James W. Useller, 
and Louis J. Chelko. April 6, 1950. 42p. diagrs., 
photos., tab. (NACA RM E9K30) 

EXPERIMENTAL INVESTIGATION OF THRUST 
AUGMENTATION OF 4000-POUND-THRUST 
CENTRIFUGAL-FLOW-TYPE TURBOJET ENGINE 
BY BLEEDOFF. William L. Jones and Louis J. 
Bogdan. July 3, 1950. 30p. diagrs., photo. 
(NACARME50D17) 



PERFORMANCE OF 4600-POUND-THRUST 
CENTRIFUGAL-FLOW-TYPE TURBOJET ENGINE 
WITH WATER-ALCOHOL INJECTION AT INLET. 
Philip W. Glasser. October 9, 1950. 24p. diagrs. 
(NACA RM E50H07) 

EFFECT OF SPARK REPETITION RATE ON THE 
IGNITION LIMITS OF A SINGLE TUBULAR COM- 
BUSTOR. Hampton H. Foster. December 1951. 
12p. diagrs., tab. (NACA RM E51J18) 

COMPARISON OF LOCKED-ROTOR AND WIND- 
MILLING DRAG CHARACTERISTICS OF AN AXIAL- 
FLOW-COMPRESSOR TYPE TURBOJET ENGINE. 
K. R. Vincent, S. C. Huntley, and H. D. Wilsted. 
January 1952. lOp. diagrs. (NACA RM E51K15) 



ANALYSIS OF COOLANT-FLOW REQUIREMENTS 
FOR AN IMPROVED, INTERNAL-STRUT - 
SUPPORTED, AIR-COOLED TURBINE-ROTOR 
BLADE. Wilson B. Schramm and Alfred J. 
Nachtigall. February 1952. 26p. .diagrs., photo. 
(NACARM E51L13) 



EXPERIMENTAL INVESTIGATION OF AIR-COOLED 
TURBINE BLADES IN TURBOJET ENGINE. XI - 
INTERNAL-STRUT-SUPPORTED ROTOR BLADE, 
Reeves P. Cochran, Francis S. Stepka, and Morton 
H. Krasner. June 1952. 45p. diagrs., photos,, 
tabs. (NACA RM E52C21) 



PRELIMINARY INVESTIGATION OF FLOW FLUC- 
TUATIONS DURING SURGE AND BLADE ROW 
STALL IN AXIAL-FLOW COMPRESSORS. Merle C. 
Huppert. August 1952. 52p. diagrs., photos. 
(NACA RM E52E28) 

TECHNIQUES FOR DETERMINING THRUST IN 
FLIGHT FOR AIRPLANES EQUIPPED WITH 
AFTERBURNERS. L. Stewart Rolls, C. Dewey 
Havill, and George R. Holden. January 1953. 27p. 
diagrs., photos. (NACA RM A52K12) 



PRELIMINARY INVESTIGATION IN J33 TURBOJET 
ENGINE OF SEVERAL ROOT DESIGNS FOR 
CERAMAL TURBINE BLADES. George C. Deutsch, 
Andre J. Meyer, Jr. and William C. Morgan. 
January 1953. 24p. diagrs. , photos. , 2 tabs. 
(NACA RM E52K13) 



COMPARATIVE TENSILE STRENGTHS AT 1200° F 
OF VARIOUS ROOT DESIGNS FOR CERMET TUR- 
BINE BLADES. Andre J. Meyer, Jr., Albert 
Kaufman, and Howard F. Calvert. June 1953. 23p. 
diagrs., photos., tabs. (NACA RM E53C25) 



ANALYTICAL EVALUATION OF EFFECT OF 
EQUIVALENCE RATIO, INLET-AIR TEMPERA- 
TURE, AND COMBUSTION PRESSURE ON PER- 
FORMANCE OF SEVERAL POSSIBLE RAM-JET 
FUELS. Leonard K. Tower and Benson E. Gammon. 
September 1953. 59p. diagrs., tabs. 
(NACA RM E53G14) 



PRELIMINARY INVESTIGATION OF THE FLOW IN 
AN ANNULAR-DIFFUSER— TAILPIPE COMBINA- 
TION WITH AN ABRUPT AREA EXPANSION AND 
SUCTION, INJECTION, AND VORTEX-GENERATOR 
FLOW CONTROLS. John R. Henry and Stafford W. 
Wilbur. February 1954. 27p. diagrs. 
(NACA RM L53K30) 



CARBON DEPOSITION OBTAINED WITH MIL-F- 
5624A FUELS IN A SINGLE COMBUSTOR AND IN 
THREE FULL-SCALE ENGINES. Jerrold D. Wear. 
June 1954. 20p. diagrs., photo., tabs. 
(NACA RM E53D15) 



127 



(3) PROPULSION 



ANALOG STUDY OF INTERACTING AND NON- 
INTERACTING MULTIPLE-LOOP CONTROL SYS- 
TEMS FOR TURBULENT ENGINES. George J. 
Pack and W. E. FhiliipB, Jr. 1955. ii, 13p. 
diagrs. (NACA Rept. 1212. Supersedes TN 3112) 



METEOROLOGICAL PROBLEMS ASSOCIATED 
WITH COMMERCIAL TUBOJET- AIRCRAFT OPER- 
ATION. A working group of the NACA Subcommittee 
on Meteorological Problems. June 1955. 46p. 
(NACA RM 54L29) 



EFFECT OF SOME SELECTED HEAT TREATMENTS 
ON THE OPERATING LIFE OF CAST HS-21 TUR- 
BINE BLADES. Francis J. Clauss, Floyd B. 
Garrett and John W. Weeton. July 1955. 39p. 
diagrs., photos. (NACA TN 3512) 



SUMMARY EVALUATION OF TOOTHED-NOZZLE 
ATTACHMENTS AS A JET -NOISE -SUPPRESSION 
DEVICE. Warren J. North. July 1955. 19p. 
diagrs., photo. (NACA TN 3516) 



APPROXIMATE METHOD FOR DETERMINING 
EQUILIBRIUM OPERATION OF COMPRESSOR 
COMPONENT OF TURBOJET ENGINE. Merle C. 
Huppert. July 1955. 25p. diagrs. (NACA TN 3517) 



OPTIMUM FLIGHT PATHS OF TURBOJET AIR- 
CRAFT. (Traiettorie Ottime Di Volo Degli Aero- 
plani Azionati Da Turboreattori). Angelo Miele. 
September 1955. 47p. diagrs. , tabs. (NACA TM 
1389. Trans, from L'Aerotecnica, v. 32, no. 4, 
1952, p. 206-219) 



EFFECT OF EXHAUST -NOZZLE EJECTORS ON 
TURBOJET NOISE GENERATION. Warren J. North 
and Willard D. Coles. October 1955. 26p. diagrs., 
photo. (NACA TN 3573) 



A SURVEY OF UNCLASSIFIED AXIAL-FLOW- 
COMPRESSOR LITERATURE. Howard Z. Herzig 
and Arthur G. Hansen. November 1955. i, 88p. 
(NACA RME55H11) 



EFFECT OF CLIMB TECHNIQUE ON JET- 
TRANSPORT NOISE. Warren J. North. January 
1956. 19p. diagrs. (NACA TN 3582) 



PERFORMANCE AND OPERATIONAL STUDIES OF 
A FULL-SCALE JET-ENGINE THRUST REVERSER. 
Robert C. Kohl. April 1956. 38p. diagrs., photo. 
(NACA TN 3665) 



A SONIC-FLOW ORIFICE PROBE FOR THE IN- 
FLIGHT MEASUREMENT OF TEMPERATURE 
PROFILES OF A JET ENGINE EXHAUST WITH 
AFTERBURNING. C. Dewey Havill and L. Stewart 
Rolls. May 1956. 18p. diagrs., photos. 
(NACA TN 3714) 



SOME LINEAR DYNAMICS OF TWO-SPOOL TURBO- 
JET ENGINES. David Novik. June 1956. 35p. 
diagrs. (NACA TN 3274) 



(3.1.4) 
TURBO -PROPELLER ENGINES 



ALTITUDE INVESTIGATION OF PERFORMANCE OF 
TURBINE-PROPELLER ENGINE AND ITS COMPO- 
NENTS. Lewis E. Wallner and Martin J. Saari. 
October 5, 1950. 65p. diagrs., photos. (NACA 
RM E50H3O) 



DYNAMIC INVESTIGATION OF TURBINE - 
PROPELLER ENGINE UNDER ALTITUDE CONDI- 
TIONS. Richard P. Krebs, Seymour C. Himmel, 
Darnold Blivas, and Harold Shames. December 6, 
1950. 55p diagrs., photo. (NACA RM E50J24) 



EVALUATION OF A SILICONE -DIESTER LUBRI- 
CANT IN BENCH STUDIES AND IN A TURBOPRO- 
PELLER ENGINE. Robert L. Johnson. S. F. 
Murray, and Edmond E. Bisson. Appendix D: 
COPY OF REPORT BY SILICONE PRODUCTS DE- 
PARTMENT OF GENERAL ELECTRIC ON NACA 
SD-17 FLUID. N. G. Holdstock, General Electric 
Company. May 1954. 32p. diagrs., photos., tabs. 
(NACA RM E54B05) 



NOISE SURVEY OF A 10-FOOT FOUR-BLADE 
TURBINE -DRIVEN PROPELLER UNDER STATIC 
CONDITIONS. MaxC. Kurbjun. July 1955. 25p. 
diagrs., photo. (NACA TN 3422) 



EFFECT OF SOME SELECTED HEAT TREATMENTS 
ON THE OPERATING LIFE OF CAST HS-21 TUR- 
BINE BLADES. Francis J. Clauss, Floyd B. 
Garrett and John W. Weeton. July 1955. 39p. 
diagrs., photos. (NACA TN 3512) 



PERFORMANCE ANALYSIS OF FDCED- AND FREE- 
TURBINE HELICOPTER ENGINES. Richard P. 
Krebs and William S. Miller, Jr. June 1956. 49p. 
diagrs. (NACA TN 3654) 



(3.1.6) 
PULSE-JET ENGINES 



INVESTIGATION OF A PULSE-JET-POWERED 
HELICOPTER ROTOR ON THE LANGLEY HELI- 
COPTER TEST TOWER. Edward J. Radin and 
PaulJ. Carpenter. February 1954. 23p. diagrs., 
photos. (NACA RM L53L15) 



INVESTIGATION OF THE PROPULSIVE CHARAC- 
TERISTICS OF A HELICOPTER-TYPE PULSE-JET 
ENGINE OVER A RANGE OF MACH NUMBERS AND 
ANGLE OF YAW. Paul J. Carpenter, James P. 
Shivers, and Edwin E. Lee, Jr. January 1956. 
24p. diagrs., photos. (NACA TN 3625) 



128 



(3) PROPULSION 



(3.1.7) 
RAM -JET ENGINES 



PERFORMANCE OF A 20-INCH STEADY-FLOW 
RAM JET AT HIGH ALTITUDES AND RAM- 
PRESSURE RATIOS. Eugene Perchonok, William H. 
Sterbentz, and Fred A. Wilcox. June 25, 1947. 39p. 
diagrs., photos. (NACA RM E6L06) 



FLIGHT INVESTIGATION OF A 20-INCH-DIAMETER 
STEADY- FLOW RAM JET. John H. Disher. 
January 14, 1948. 29p. diagrs., photo. 
(NACA RM E7I05a) 



SOME EFFECTS OF GUTTER FLAME -HOLDER 
DIMENSIONS ON COMBUSTION-CHAMBER PER- 
FORMANCE OF 20 -INCH RAM JET. Fred A. 
Wilcox, Eugene Perchonok, and George Wishnek. 
July 30, 1948. 39p. diagrs., photos., tab. 
(NACA RM E8C22) 



EFFECT OF THREE FLAME-HOLDER CONFIGU- 
RATIONS ON SUBSONIC FLIGHT PERFORMANCE 
OF RECTANGULAR RAM JET OVER RANGE OF 
ALTITUDES. Dugald O. Black and Wesley E. 
Messing. November 24, 1948. 28p. diagrs., photo, 
tab. (NACA RM E8I01) 



EFFECT OF VARIATION IN FUEL PRESSURE ON 
COMBUSTION PERFORMANCE OF RECTANGULAR 
RAM JET. Wesley E. Messing and Dugald O. Black. 
November 24, 1948. 26p. diagrs., photo., tab. 
(NACA RM E8I28) 



DESIGN FACTORS FOR 4- BY 8-INCH RAM-JET 
COMBUSTOR. Donald W. Male and Adolph J. 
Cervenka. August 11, 1949. 47p. diagrs., photos. 
(NACA RM E9F09) 



INVESTIGATION OF INTERNAL REGENERATIVE 
FUEL-HEATING SYSTEM FOR 20-INCH RAM JET. 
Sol Baker and Eugene Perchonok. September 1, 
1949. 22p. diagrs., photos. (NACA RM E9F20) 



FREE-FLIGHT PERFORMANCE OF 16-INCH- 
DIAMETER SUPERSONIC RAM-JET UNITS. I - 
FOUR UNITS DESIGNED FOR COMBUSTION - 
CHAMBER-INLET MACH NUMBER OF 0.12 AT 
FREE-STREAM MACH NUMBER OF 1.6 (UNITS A-2, 
A-3, A-4, AND A-5). William W. Carlton and 
Wesley E. Messing. September 22, 1949. 51p. 
diagrs., photos. (NACA RM E9F22) 



ANALYSIS AND EXPERIMENTAL OBSERVATION OF 
PRESSURE LOSSES IN RAM -JET COMBUSTION 
CHAMBERS. William H. Sterbentz. November 4, 
1949. 22p. diagrs. (NACA RM E9H19) 



INITIAL FLIGHT INVESTIGATION OF A TWIN- 
ENGINE SUPERSONIC RAM JET. Maxime A. Faget 
andH. Rudolph Dettwyler. September 15, 1950. 
28p. diagrs., photos. (NACA RM L50H10) 



FREE-JET PERFORMANCE OF 16-INCH RAM-JET 
ENGINE WITH SEVERAL FUELS. Fred A. Wilcox. 
October 31, 1950. 23p. diagrs., photos. 
(NACA RM E50I06) 



FREE-JET TESTS OF A 6.5-INCH-DIAMETER 
RAM-JET ENGINE AT MACH NUMBERS OF 1.81 
AND 2.00. Maxime A. Faget, Raymond S. Watson, 
and Walter A. Bartlett, Jr. March 7, 1951. 38p. 
diagrs., photos. (NACA RM L50L06) 



PRELIMINARY EVALUATION OF THE AIR AND 
FUEL SPECIFIC-IMPULSE CHARACTERISTICS OF 
SEVERAL POTENTIAL RAM-JET FUELS. I - 
OCTENE-1, ALUMINUM, AND ALUMINUM - 
OCTENE-1 SLURRIES. Benson E. Gammon. 
April 30, 1951. 20p. diagrs. (NACA RM E51C12) 



PRELIMINARY EVALUATION OF THE AIR AND 
FUEL SPECIFIC-IMPULSE CHARACTERISTICS OF 
SEVERAL POTENTIAL RAM-JET FUELS. II - 
MAGNESIUM AND MAGNESIUM - OCTENE-1 
SLURRIES. Benson E. Gammon. May 2, 1951. 
15p. diagrs. (NACA RM E51C23) 



PRELIMINARY INVESTIGATION OF HELMHOLTZ 
RESONATORS FOR DAMPING PRESSURE FLUCTU- 
ATIONS IN 3.6-INCH RAM JET AT MACH NUMBER 
1.90. Jerome L. Fox. May 22, 1951. 24p. diagrs., 
photos. (NACA RM E51C05) 



PRELIMINARY EVALUATION OF THE AIR AND 
FUEL SPECIFIC -IMPULSE CHARACTERISTICS OF 
SEVERAL POTENTIAL RAM-JET FUELS. 01 - 
DIBORANE, PENTABORANE, BORON, AND BORON- 
OCTENE-1 SLURRIES. Benson E. Gammon. July 
1951. 26p. diagrs. (NACA RM E51D25) 



PRELIMINARY EVALUATION OF THE AIR AND 
FUEL SPECIFIC -IMPULSE CHARACTERISTICS OF 
SEVERAL POTENTIAL RAM-JET FUELS. IV- 
HYDROGEN, a-METHYLNAPHTHALENE, AND 
CARBON. Benson E. Gammon. August 1951. 22p. 
diagrs. (NACA RM E51F05) 



ANALYTICAL INVESTIGATION OF RAM-JET EN- 
GINE PERFORMANCE IN FLIGHT MACH NUMBER 
RANGE FROM 3 TO 7. Philip J. Evans, Jr. 
October 1951. 29p. diagrs. (NACA RM E51H02) 



FREE-JET TESTS OF A 1.1-INCH-DIAMETER 
SUPERSONIC RAM-JET ENGINE. Joseph H. Judd 
and Otto F. Trout, Jr. March 1952. 24p. diagrs., 
photos., tabs. (NACA RM L51L18) 



EFFECT OF FUEL-AIR DISTRIBUTION ON PER- 
FORMANCE OF A 16-INCH RAM-JET ENGINE. 
A. J. Cervenka and E. E. Dangle. June 1952. 
25p. diagrs., photos., tab. (NACA RM E52D08) 



FLIGHT MEASUREMENTS AT MACH NUMBERS 
FROM 1.1 TO 1.9 OF THE ZERO-LIFT DRAG OF A 
TWIN-ENGINE SUPERSONIC RAM-JET CONFIGU- 
RATION. Abraham Leiss. June 1952. 16p. 
diagrs., photos. (NACA RM L52D24) 



129 



(3) PROPULSION 



COMBUSTION EFFICIENCY OF HOMOGENEOUS 
FUEL-AIR MIXTURES IN A 5-INCH RAM-JET- 
TYPE COMBUSTOR. Thaine W. Reynolds and 
Robert D. Inrebo. November 1952. 36d. diagrs. 
tabs. (NACA RM E52I23) 



SUMMARY REPORT ON ANALYTICAL EVALUATION 
OF AIR AND FUEL SPECIFIC -IMPULSE CHARAC- 
TERISTICS OF SEVERAL NONHYDROCARBON JET- 
ENGINE FUELS. Roland Breitwieser, Sanford 
Gordon and Benson Gammon. February 1953. 
58p. diagrs., tab. (NACA RM E52L08) 



EFFECT OF FUELS ON COMBUSTION EFFICIENCY 
OF 5-INCH RAM-JET-TYPE COMBUSTION. 
Thaine W. Reynolds. May 1953. 40p. diagrs., 
tabs. (NACA RM E53C20) 



ANALYTICAL EVALUATION OF EFFECT OF 
EQUIVALENCE RATIO, INLET-AIR TEMPERA- 
TURE, AND COMBUSTION PRESSURE ON PER- 
FORMANCE OF SEVERAL POSSIBLE RAM-JET 
FUELS. Leonard K. Tower and Benson E. Gammon. 
September 1953. 59p. diagrs., tabs. 
(NACA RM E53G14) 



THEORETICAL AND EXPERIMENTAL INVESTIGA- 
TION OF ADDITIVE DRAG. Merwin Sibulkin. 1954. 
ii, 12p. diagrs. (NACA Rept. 1187. Formerly 
RM E51B13) 



ACOUSTIC ANALYSIS OF RAM-JET BUZZ. 
Mirels. November 1955. 33p diagrs. 
(NACA TN 3574) 



Harold 



EVAPORATION OF JP-5 FUEL SPRAYS IN AIR 
STREAMS. Hampton H. Foster and Robert D. 
Ingebo. February 1956. 26p. diagrs., tabs. 
(NACA RM E55K02) 



EFFECT OF TRANSVERSE BODY FORCE ON CHAN- 
NEL FLOW WITH SMALL HEAT ADDITION. Simon 
Ostrach and Franklin K. Moore. February 1956. 
31p. diagrs. (NACA TN 3594) 



(3.1.8) 
ROCKET ENGINES 



THEORETICAL PERFORMANCE OF SOME ROCKET 
PROPELLANTS CONTAINING HYDROGEN, 
NITROGEN, AND OXYGEN, Riley O. Miller and 
Paul M. Ordin. May 26, 1948. 53p. diagrs., tabs. 
(NACA RM E8A30) 



STARTING OF ROCKET ENGINE AT CONDITIONS 
OF SIMULATED ALTITUDE USING CRUDE MONO- 
ETHYLANILINE AND OTHER FUELS WITH MLXED 
ACID. Dezso J- Ladanyi, John L. Sloop, Jack C. 
Humphrey, and Gerald Morrell. July 19, 1950. 
64p. diagrs., photos., tabs. (NACA RM E50D20) 

ORTHOTOLUIDINE AND TRIETHYLAMINE IN 
ROCKET ENGINE APPLICATIONS. Dezso J. 
Ladanyt. January 1953. 24p. diagrs., tabs. 
(NACARM E52K19) 



COMPARISON OF IGNITION DELAYS OF SEVERAL 
PROPELLANT COMBINATIONS OBTAINED WITH 
MODIFIED OPEN-CUP AND SMALL-SCALE ROCK- 
ET ENGINE APPARATUS. Dezso J. Ladanyi and 
Riley 0. Miller. June 1953. 20p. diagrs., photos., 
tabs. (NACA RM E53D03) 



THEORETICAL PERFORMANCE OF JP-4 FUEL 
AND LIQUID OXYGEN AS A ROCKET PROPEL- 
LANT. I - FROZEN COMPOSITION. Vearl N. Huff 
and Anthony Fortini. April 1956. 35p. diagrs., 
tabs. (NACA RM E56A27) 



(3.1.9) 
JET- DRIVEN ROTORS 



INVESTIGATION OF A PULSE-JET-POWERED 
HELICOPTER ROTOR ON THE LANGLEY HELI- 
COPTER TEST TOWER. Edward J. Radin and 
Paul J. Carpenter. February 1954. 23p, diagrs.. 
photos. (NACA RM L53L15) 



LAMINAR FREE CONVECTION ON A VERTICAL 
PLATE WITH PRESCRIBED NONUNIFORM WALL 
HEAT FLUX OR PRESCRIBED NONUNIFORM WALL 
TEMPERATURE. E. M. Sparrow. July 1955. 34p. 
diagrs. (NACA TN 3508) 



EFFECT OF TRANSVERSE BODY FORCE ON CHAN- 
NEL FLOW WITH SMALL HEAT ADDITION. Simon 
Ostrach and Franklin K. Moore. February 1956. 
3lp. diagrs. (NACA TN 3594) 



(3.1.10) 
NUCLEAR-ENERGY SYSTEMS 



VISUAL STUDY OF FREE CONVECTION IN A 
NARROW VERTICAL ENCLOSURE. Ephraim M. 
Sparrow and Samuel J. Kaufman. February 1956. 
14p. diagr., photos. (NACA RM E55L14a) 



SELF SHIELDING IN RECTANGULAR AND CYLIN- 
DRICAL GEOMETRIES. Harold Schneider, Paul G. 
Saper, and Charles F. Kadow. April 1956. 40p. 
diagrs., tabs. (NACA TN 3661) 



130 

(3) PROPULSION 



(3.2) 
Control of Engines 



SUMMARY OF SCALE-MODEL THRUST-REVERSER 
INVESTIGATION. John H. Povolny, Fred W. 
Steffen, and Jack G. McArdle. February 1956. 
49p. diagrs., photos. (NACA TN 3664) 



(3.2.2) 
CONTROL OF TURBOJET ENGINES 



COMPARISON OF LOCKED-ROTOR AND WIND- 
MILLING DRAG CHARACTERISTICS OF AN AXIAL- 
FLOW-COMPRESSOR TYPE TURBOJET ENGINE. 
K R. Vincent, S. C. Huntley, and H. D. W listed. 
January 1952. lOp. diagrs. (NACA RM E51K15) 

ANALOG STUDY OF INTERACTING AND NON- 
INTERACTING MULTIPLE-LOOP CONTROL SYS- 
TEMS FOR TURBULENT ENGINES. George J. 
Pack and W. E. Phillips, Jr. 1955. ii, 13p. 
diagrs. (NACA Rept. 1212. Supersedes TN 3112) 



SOME LINEAR DYNAMICS OF TWO-SPOOL TURBO- 
JET ENGINES. David Novik. June 1956. 35p. 
diagrs. (NACA TN 3274) 

(3.2.4) 

CONTROL OF 

TURBINE-PROPELLER ENGINES 

DYNAMIC INVESTIGATION OF TURBINE - 
PROPELLER ENGINE UNDER ALTITUDE CONDI- 
TIONS. Richard P. Krebs, Seymour C. Himmel, 
Darnold Blivas, and Harold Shames. December 6, 
1950. 55p diagrs., photo. (NACA RM E50J24) 



131 



(3) PROPULSION 



(3.3) 
Auxiliary Booster Systems 



EXPERIMENTAL INVESTIGATION OF THRUST 
AUGMENTATION OF 4000- POUND -THRUST 
CENTRIFUGAL- FLOW -TYPE TURBOJET ENGINE 
BY BLEEDOFF. William L. Jones and Louis J. 
Bogdan. July 3, 1950. 30p. diagrs., photo. 
(NACARME50D17) 



(3.3.2) 
GAS TURBINES 

(3. 3. 2. 1) 
LIQUID INJECTION 

EXPERIMENTAL INVESTIGATION OF THRUST 
AUGMENTATION OF 4000-POUND-THRUST AXIAL- 
FLOW-TYPE TURBOJET ENGINE BY INTERSTAGE 
INJECTION OF WATER-ALCOHOL MIXTURES IN 
COMPRESSOR. John H. Povolny, James W. Useller, 
and Louis J. Chelko. April 6, 1950. 42p. diagrs., 
photos., tab. (NACA RM E9K30) 



EXPERIMENTAL INVESTIGATION OF THRUST 
AUGMENTATION OF 4000-POUND-THRUST 
CENTRIFUGAL- FLOW-TYPE TURBOJET ENGINE 
BY BLEEDOFF. William L. Jones and Louis J. 
Bogdan. July 3, 1950. 30p. diagrs., photo. 
(NACA RM E50D17) 



PERFORMANCE OF 4600- POUND-THRUST 
CENTRIFUGAL- FLOW-TYPE TURBOJET ENGINE 
WITH WATER-ALCOHOL INJECTION AT INLET. 
Philip W. Glasser. October 9, 1950. 24p. diagrs. 
(NACA RM E50H07) 



(3. 3.2.2) 
AFTERBURNING 



IDEAL TEMPERATURE RISE DUE TO CONSTANT - 
PRESSURE COMBUSTION OF A JP-4 FUEL. 
S(idney) C. Huntley. September 1955. 53p. 
diagrs., tabs. (NACA RM E55G27a) 



(3.3.2. 3) 
BLEEDOFF 



PERFORMANCE INVESTIGATION OF CAN-TYPE 
COMBUSTOR, II - WATER INJECTION AT VARI- 
OUS STATIONS IN COMBUSTOR. William P. Cook 
and Eugene V. Zettle. September 30, 1948. 27p. 
diagrs. (NACA RM E8F28) 



EXPERIMENTAL INVESTIGATION OF THRUST 
AUGMENTATION OF 4000-POUND-THRUST 
CENTRIFUGAL-FLOW-TYPE TURBOJET ENGINE 
BY BLEEDOFF. William L. Jones and Louis J. 
Bogdan. July 3, 1950. 30p. diagrs., photo. 
(NACARME50D17) 



132 

(3) PROPULSION 



(3.4) 
Fuels 



LOW-TEMPERATURE IGNITION-DELAY CHARAC- 
TERISTICS OF SEVERAL ROCKET FUELS WITH 
MIXED ACID IN MODIFIED OPEN-CUP-TYPE AP- 
PARATUS. Riley O. Miller. October 17, 1950. 
23p. diagrs., photos., tabs. (NACA RM E50H16) 



CONSIDERATIONS IN THE ADAPTATION OF LOW- 
COST FUELS TO GAS-TURBINE-POWERED COM- 
MERCIAL AIRCRAFT. Henry C. Barnett and 
Richard J. McCalferty. October 1953. 59p. diagrs. , 
photo., 2 tabs. (NACA RM E53H05) 



CHEMICAL ACTION OF HALOGENATED AGENTS 
IN FIRE EXTINGUISHING. Frank E. Belles. 
September 1955. 28p. diagrs., 3 tabs. (NACA 
TN 3565) 



(3.4.1) 
PREPARATION 



SOME FUNDAMENTAL ASPECTS OF NITRIC ACID 
OXIDANTS FOR ROCKET APPLICATIONS. Dezso J. 
Ladanyi, Riley O, Miller, Wolf Karo, and Charles E. 
Feiler. January 1953. ii, 95p. diagrs., tabs. 
(NACA RM E52J01) 



EXPERIMENTAL AND CALCULATED TEMPERA- 
TURE AND MASS HISTORIES OF VAPORIZING 
FUEL DROPS. M. M. El Wakil, R. J. Priem, 
H. J. Brikowski, P. S. Myers, and O. A. Uyehara, 
Wisconsin University. January 1956. 82p. diagrs., 
photos., tab. (NACA TN 3490) 



EVAPORATION OF JP-5 FUEL SPRAYS IN AIR 
STREAMS. Hampton H. Foster and Robert D. 
Ingebo. February 1956. 26p. diagrs., tabs. 
(NACA RM E55K02) 



(3.4.2) 

PHYSICAL AND CHEMICAL 

PROPERTIES 



THEORETICAL PERFORMANCE OF SOME ROCKET 
PROPELLANTS CONTAINING HYDROGEN, 
NITROGEN, AND OXYGEN. Riley O. Miller and 
Paul M. Ordin. May 26. 1948. 53p. diagrs., tabs. 
(NACA RM E8A30) 



LOW-TEMPERATURE IGNITION-DELAY CHARAC- 
TERISTICS OF SEVERAL ROCKET FUELS WITH 
MDCED ACID IN MODIFIED OPEN-CUP-TYPE AP- 
PARATUS. Riley O. Miller. October 17, 1950. 
23p. diagrs., photos., tabs. (NACA RM E50H16) 



IGNITION -DELAY CHARACTERISTICS IN MODIFIED 
OPEN-CUP APPARATUS OF SEVERAL FUELS 
WITH NITRIC ACID OXIDANTS WITHIN TEMPERA- 
TURE RANGE 70° TO -105° F. Riley O. Miller. 
December 1951. 30p. diagrs., 4 tabs. 
(NACA RM E51J11) 



EFFECT OF SPARK REPETITION RATE ON THE 
IGNITION LIMITS OF A SINGLE TUBULAR COM- 
BUSTOR. Hampton H. Foster. December 1951. 
12p. diagrs., tab. (NACA RM E51J18) 



IGNITION DELAY EXPERIMENTS WITH SMALL- 
SCALE ROCKET ENGINE AT SIMULATED ALTI- 
TUDE CONDITIONS USING VARIOUS FUELS WITH 
NITRIC ACID OXIDANTS. Dezso J. Ladanyi. 
January 1952. 44p. diagrs., photos., tabs. 
(NACARM E51J01) 



SOME FUNDAMENTAL ASPECTS OF NITRIC ACID 
OXIDANTS FOR ROCKET APPLICATIONS. Dezso J. 
Ladanyi, Riley O. Miller, Wolf Karo, and Charles E. 
Feiler. January 1953. ii, 95p. diagrs., tabs. 
(NACA RM E52J01) 



ORTHOTOLUIDINE AND TRIETHYLAMINE IN 
ROCKET ENGINE APPLICATIONS. Dezso J. 
Ladanyi. January 1953. 24p. diagrs., tabs. 
(NACA RM E52K19) 



COMPARISON OF IGNITION DELAYS OF SEVERAL 
PROPELLANT COMBINATIONS OBTAINED WITH 
MODIFIED OPEN-CUP AND SMALL-SCALE ROCK- 
ET ENGINE APPARATUS. Dezso J. Ladanyi and 
Riley O. Miller. June 1953. 20p. diagrs., photos., 
tabs. (NACA RM E53D03) 



EFFECTS OF NITROGEN TETROXIDE AND WATER 
CONCENTRATION ON FREEZING POINT AND IGNI- 
TION DELAY OF FUMING NITRIC ACID. Riley O. 
Miller. September 1953. 32p. diagrs., tabs. 
(NACA RM E53G31) 



CONSIDERATIONS IN THE ADAPTATION OF LOW- 
COST FUELS TO GAS -TURBINE -POWERED COM- 
MERCIAL AIRCRAFT. Henry C. Barnett and 
Richard J. McCafferty. October 1953. 59p. diagrs., 
photo., 2 tabs. (NACA RM E53H05) 



INVESTIGATION OF EFFECT OF FLUORIDE ON 
CORROSION OF 2S-0 ALUMINUM AND 347 STAIN- 
LESS STEEL IN FUMING NITRIC ACID AT 170° F. 
Charles E. Feiler and Gerald Morrell. February 
1954. 22p. diagrs., photos., tabs. 
(NACA RM E53L17b) 



CARBON DEPOSITION OBTAINED WITH MIL-F- 
56 24 A FUELS IN A SINGLE COMBUSTOR AND IN 
THREE FULL-SCALE ENGINES. Jerrold D. Wear. 
June 1954. 20p. diagrs., photo., tabs. 

(NACARM E53D15) 



133 



(3) PROPULSION 



AN AUTOMATIC VISCOMETER FOR NON- 
NEWTONIAN MATERIALS. Ruth N. Weltmann and 
Perry W. Kuhns. August 1955. 34p. diagrs., 
photos., tab. (NACA TN 3510) 



AVERAGE BOND ENERGIES BETWEEN BORON 
AND ELEMENTS OF THE FOURTH, FIFTH, SIXTH, 
AND SEVENTH GROUPS OF THE PERIODIC TABLE. 
Aubrey P. Altshuller. November 1955. 7p. tab. 
(NACA RM E55I27a) 



EFFECT OF DISSOLVED OXYGEN ON THE FIL- 
TERABILITY OF JET FUELS FOR TEMPERA- 
TURES BETWEEN 300° AND 400° F. Anderson B. 
McKeown and Robert R. Hibbard. December 1955. 
22p. diagrs., photos., tabs. (NACA RM E55I28) 



EXPERIMENTAL AND CALCULATED TEMPERA- 
TURE AND MASS HISTORIES OF VAPORIZING 
FUEL DROPS. M. M. El Wakil, R. J. Priem, 
H. J. Brikowski, P. S. Myers, and O. A. Uyehara, 
Wisconsin University. January 1956. 82p. diagrs., 
photos., tab. (NACA TN 3490) 



THEORETICAL PERFORMANCE OF JP-4 FUEL 
AND LIQUID OXYGEN AS A ROCKET PROPEL- 
LANT. I - FROZEN COMPOSITION. Vearl N. Huff 
and Anthony Fortini. April 1956. 35p. diagrs., 
tabs. (NACA RM E56A27) 



VAPOR-PHASE OXIDATION AND SPONTANEOUS 
IGNITION - CORRELATION AND EFFECT OF VARI- 
ABLES. Donald E. Swarts and Milton Or chin, 
University of Cincinnati. April 1956. 32p. diagrs., 
tabs. (NACA TN 3579) 



PRELIMINARY EVALUATION OF THE AIR AND 
FUEL SPECIFIC-IMPULSE CHARACTERISTICS OF 
SEVERAL POTENTIAL RAM-JET FUELS. I - 
OCTENE-1, ALUMINUM, AND ALUMINUM - 
OCTENE-1 SLURRIES. Benson E. Gammon. 
April 30. 1951. 20p. diagrs. (NACA RM E51C12) 



PRELIMINARY EVALUATION OF THE AIR AND 
FUEL SPECIFIC-IMPULSE CHARACTERISTICS OF 
SEVERAL POTENTIAL RAM-JET FUELS. H - 
MAGNESIUM AND MAGNESIUM - OCTENE-1 
SLURRIES. Benson E. Gammon. May 2, 1951. 
15p. diagrs. (NACA RM E51C23) 



(3.4.3) 

RELATION TO ENGINE 

PERFORMANCE 



PRELIMINARY EVALUATION OF THE AIR AND 
FUEL SPECIFIC -IMPULSE CHARACTERISTICS OF 
SEVERAL POTENTIAL RAM-JET FUELS. HI - 
DIBORANE, PENTABORANE, BORON, AND BORON- 
OCTENE-1 SLURRIES. Benson E. Gammon. July 
1951. 26p. diagrs. (NACA RM E51D25) 



PREUMINARY EVALUATION OF THE AIR AND 
FUEL SPECIFIC -IMPULSE CHARACTERISTICS OF 
SEVERAL POTENTIAL RAM-JET FUELS. IV - 
HYDROGEN, a-METHYLNAPHTHALENE, AND 
CARBON. Benson E. Gammon. August 1951. 22p. 
diagrs. (NACA RM E51F05) 



EFFECT OF SPARK REPETITION RATE ON THE 
IGNITION LIMITS OF A SINGLE TUBULAR COM- 
BUSTOR. Hampton H. Foster. December 1951. 
12p. diagrs., tab. (NACA RM E51J18) 



COMBUSTION EFFICIENCY OF HOMOGENEOUS 
FUEL-AIR MIXTURES IN A 5-INCH RAM-JET- 
TYPE COMBUSTOR. Thaine W. Reynolds and 
Robert D. Ingebo. November 1952. 36p. diagrs., 
tabs. (NACA RM E52I23) 



ORTHOTOLUIDINE AND TRIETHYLAMINE IN 
ROCKET ENGINE APPLICATIONS. Dezso J. 
Ladanyl. January 1953. 24p. diagrs., tabs. 
(NACA RM E52K19) 



SUMMARY REPORT ON ANALYTICAL EVALUATION 
OF AIR AND FUEL SPECIFIC -IMPULSE CHARAC- 
TERISTICS OF SEVERAL NONHYDROCARBON JET- 
ENGINE FUELS. Roland Breitwieser, Sanford 
Uordon and Benson Gammon. February 1953. 
58p." diagrs., tab. (NACA RM E52L08) 



EFFECT OF FUELS ON COMBUSTION EFFICIENCY 
OF 5 -INCH RAM- JET-TYPE COMBUSTION. 
Thaine W. Reynolds. May 1953. 40p. diagrs., 
tabs. (NACA RM E53C20) 



COMPARISON OF IGNITION DELAYS OF SEVERAL 
PROPELLANT COMBINATIONS OBTAINED WITH 
MODIFIED OPEN-CUP AND SMALL-SCALE ROCK- 
ET ENGINE APPARATUS. Dezso J. Ladanyl and 
RUey 0. Miller. June 1953. 20p. diagrs., photos., 
tabs. (NACA RM E53D03) 



ANALYTICAL EVALUATION OF EFFECT OF 
EQUIVALENCE RATIO, INLET-AIR TEMPERA- 
TURE, AND COMBUSTION PRESSURE ON PER- 
FORMANCE OF SEVERAL POSSIBLE RAM-JET 
FUELS. Leonard K. Tower and Benson E. Gammon. 
September 1953. 59p. diagrs., tabs. 
(NACARM E53G14) 



CARBON DEPOSITION OBTAINED WITH MIL-F- 
5624A FUELS IN A SINGLE COMBUSTOR AND IN 
THREE FULL-SCALE ENGINES. Jerrold D. Wear. 
June 1954. 2 Op. diagrs., photo., tabs. 
(NACARM E53D15) 



EFFECT OF DISSOLVED OXYGEN ON THE FIL- 
TERABILITY OF JET FUELS FOR TEMPERA- 
TURES BETWEEN 300° AND 400° F. Anderson B. 
McKeown and Robert R. Hibbard. December 1955. 
22p. diagrs., photos., tabs. (NACA RM E55I28) 



134 



(3) PROPULSION 



(3.4. 3.2) 

TURBINE ENGINES, RAM JETS, 

AND PULSE JETS 



FREE-JET PERFORMANCE OF 16-INCH RAM-JET 
ENGINE WITH SEVERAL FUELS. Fred A. Wilcox. 
October 31, 1950. 23p. diagrs., photos. 
(NACA RM E50I06) 



FLAME VELOCITIES OF FOUR ALKYLSILANES. 
Melvin Gerstein, Edgar L. Wong, and Oscar Levine. 
March 9, 1951. 14p. diagrs., tab. 
(NACA RM E51A08) 



PRELIMINARY EVALUATION OF THE AIR AND 
FUEL SPECIFIC -IMPULSE CHARACTERISTICS OF 
SEVERAL POTENTIAL RAM-JET FUELS. I - 
OCTENE-1, ALUMINUM, AND ALUMINUM - 
OCTENE-1 SLURRIES. Benson E. Gammon. 
April 30. 1951. 20p. diagrs. (NACA RM E51C12) 



PRELIMINARY EVALUATION OF THE AIR AND 
FUEL SPECIFIC-IMPULSE CHARACTERISTICS OF 
SEVERAL POTENTIAL RAM-JET FUELS. II - 
MAGNESIUM AND MAGNESIUM - OCTENE-1 
SLURRIES. Benson E. Gammon. May 2, 1951. 
15p. diagrs. (NACA RM E51C23) 



PRELIMINARY EVALUATION OF THE AIR AND 
FUEL SPECIFIC -IMPULSE CHARACTERISTICS OF 
SEVERAL POTENTIAL RAM-JET FUELS. HI - 
DIBORANE, PENTABORANE, BORON, AND BORON - 
OCTENE-1 SLURRIES. Benson E. Gammon. July 
1951. 26p. diagrs. (NACA RM E51D25) 



PRELIMINARY EVALUATION OF THE AIR AND 
FUEL SPECIFIC -IMPULSE CHARACTERISTICS OF 
SEVERAL POTENTIAL RAM-JET FUELS. IV - 
HYDROGEN, a-METHYLNAPHTHALENE, AND 
CARBON. Benson E. Gammon. August 1951. 22p. 
diagrs. (NACA RM E51F05) 



EFFECT OF SPARK REPETITION RATE ON THE 
IGNITION LIMITS OF A SINGLE TUBULAR COM- 
BUSTOR. Hampton H. Foster. December 1951. 
12p. diagrs., tab. (NACA RM E51J18) 



EFFECT OF INLET-AIR AND FUEL PARAMETERS 
ON SMOKING CHARACTERISTICS OF A SINGLE 
TUBULAR TURBOJET-ENGINE COMBUSTOR. 
Helmut F. Butze. April 1952. 26p. diagrs.. 
photos., tabs. (NACA RM E52A18) 



EFFECT OF OXYGEN CONCENTRATION OF THE 
INLET OXYGEN-NITROGEN MIXTURE ON THE 
COMBUSTION EFFICIENCY OF A SINGLE J33 
TURBOJET COMBUSTOR. Charles C. Graves. 
August 1952. 45p. diagrs., 2 tabs. 
(NACA RME52F13) 



COMBUSTION EFFICIENCY OF HOMOGENEOUS 
FUEL-AIR MIXTURES IN A 5-INCH RAM-JET- 
TYPE COMBUSTOR. Thaine W. Reynolds and 
Robert D. Ingebo. November 1952. 3Cp. diagrs., 
tabs. (NACA RM E52I23) 



SUMMARY REPORT ON ANALYTICAL EVALUATION 
OF AIR AND FUEL SPECIFIC -IMPULSE CHARAC- 
TERISTICS OF SEVERAL NONHYDROCARBON JET- 
ENGINE FUELS. Roland Breitwieser, Sanford 
Gordon and Benson Gammon. February 1953. 
58p. diagrs., tab. (NACA RM E52L08) 



EFFECT OF INLET OXYGEN CONCENTRATION ON 
COMBUSTION EFFICIENCY OF J33 SINGLE COM- 
BUSTOR OPERATING WITH GASEOUS PROPANE. 
Charles C. Graves. March 1953. 22p. diagrs., 
tab. (NACA RM E53A27) 



EFFECT OF FUELS ON COMBUSTION EFFICIENCY 
OF 5-INCH RAM-JET-TYPE COMBUSTION. 
Thaine W. Reynolds. May 1953. 40p. diagrs., 
tabs. (NACA RM E53C20) 



ANALYTICAL EVALUATION OF EFFECT OF 
EQUIVALENCE RATIO, INLET-AIR TEMPERA- 
TURE, AND COMBUSTION PRESSURE ON PER- 
FORMANCE OF SEVERAL POSSIBLE RAM- JET 
FUELS. Leonard K. Tower and Benson E. Gammon. 
September 1953. 59p. diagrs., tabs. 
(NACA RM E53G14) 



CONSIDERATIONS IN THE ADAPTATION OF LOW- 
COST FUELS TO GAS-TURBINE-POWERED COM- 
MERCIAL AIRCRAFT. Henry C. Barnett and 
Richard J. McCafferty. October 1953. 59p. diagrs., 
photo., 2 tabs. (NACA RM E53H05) 



CARBON DEPOSITION OBTAINED WITH MIL-F- 
5624A FUELS IN A SINGLE COMBUSTOR AND IN 
THREE FULL-SCALE ENGINES. Jerrold D. Wear. 
June 1954. 20p. diagrs., photo., tabs. 
(NACARME53D15) 



IDEAL TEMPERATURE RISE DUE TO CONSTANT- 
PRESSURE COMBUSTION OF A JP-4 FUEL. 
S(idney) C. Huntley. September 1955. 53p. 
diagrs., tabs. (NACA RM E55G27a) 



EXPERIMENTAL AND CALCULATED TEMPERA- 
TURE AND MASS HISTORIES OF VAPORIZING 
FUEL DROPS. M. M. El Wakil, R. J. Priem, 
H. J. Brikowski, P. S. Myers, and O. A. Uyehara, 
Wisconsin University. January 1956. 82p. diagrs., 
photos., tab. (NACA TN 3490) 



EVAPORATION OF JP-5 FUEL SPRAYS IN AIR 
STREAMS. Hampton H. Foster and Robert D. 
Ingebo. February 1956. 26p. diagrs., tabs. 
(NACA RM E55K02) 



(3.4. 3. 3) 
ROCKETS (INCLUDES FUEL 

AND OXIDANT) 



THEORETICAL PERFORMANCE OF SOME ROCKET 
PROPELLANTS CONTAINING HYDROGEN, 
NITROGEN, AND OXYGEN. Riley O. Miller and 
Paul M. Ordin. May 26 f 1948. 53p. diagrs., tabs. 
(NACA RM E8A30) 



135 



(3) PROPULSION 



STARTING OF ROCKET ENGINE AT CONDITIONS 
OF SIMULATED ALTITUDE USING CRUDE MONO- 
ETHYLANILINE AND OTHER FUELS WITH MIXED 
ACID. Dezso J. Ladanyi, John L. Sloop, Jack C. 
Humphrey, and Gerald Morrell. July 19, 1950. 
64p. diagrs., photos., tabs. (NACA RM E50D20) 



LOW-TEMPERATURE IGNITION -DELAY CHARAC- 
TERISTICS OF SEVERAL ROCKET FUELS WITH 
MDCED ACID IN MODIFIED OPEN-CUP-TYPE AP- 
PARATUS. Riley O, Milter. October 17, 1950. 
23p. diagrs,, photos., tabs. (NACA RM E50H16) 



IGNITION -DELAY CHARACTERISTICS IN MODIFIED 
OPEN-CUP APPARATUS OF SEVERAL FUELS 
WITH NITRIC ACID OXIDANTS WITHIN TEMPERA- 
TURE RANGE 70° TO -105° F. Riley O. Miller. 
December 1951. 30p. diagrs., 4 tabs. 
(NACA RME51J11) 



IGNITION DELAY EXPERIMENTS WITH SMALL- 
SCALE ROCKET ENGINE AT SIMULATED ALTI- 
TUDE CONDITIONS USING VARIOUS FUELS WITH 
NITRIC ACID OXIDANTS. Dezso J. Ladanyi. 
January 1952. 44p. diagrs., photos., tabs. 
(NACA RM E51J01) 



INVESTIGATION OF EFFECTS OF ADDITIVES ON 
STORAGE PROPERTIES OF FUMING NITRIC ACIDS. 
Charles E. Feiler and Gerald Morrell. December 
1952. 25p. photos., diagrs., tabs. 
(NACA RM E52JT16) 



SOME FUNDAMENTAL ASPECTS OF NITRIC ACID 
OXIDANTS FOR ROCKET APPLICATIONS. Dezso J. 
Ladanyi, Riley O. Miller, Wolf Karo, and Charles E. 
Feiler. January 1953. il, 95p. diagrs., tabs. 
(NACA RM E52J01) 



ORTHOTOLUIDINE AND TRIETHYLAMINE IN 
ROCKET ENGINE APPLICATIONS. Dezso J. 
Ladanyi. January 1953. 24p. diagrs., tabs. 
(NACA RM E52K19) 



COMPARISON OF IGNITION DELAYS OF SEVERAL 
PROPELLANT COMBINATIONS OBTAINED WITH 
MODIFIED OPEN-CUP AND SMALL-SCALE ROCK- 
ET ENGINE APPARATUS. Dezso J. Ladanyi and 
Riley O. Miller. June 1953. 20p. diagrs., photos., 
tabs. (NACA RM E53D03) 



EFFECTS OF NITROGEN TETROXIDE AND WATER 
CONCENTRATION ON FREEZING POINT AND IGNI- 
TION DELAY OF FUMING NITRIC ACID. Riley O. 
Miller. September 1953. 32p. diagrs., tabs. 
(NACA RM E53G31) 



INVESTIGATION OF EFFECT OF FLUORIDE ON 
CORROSION OF 2S-0 ALUMINUM AND 347 STAIN- 
LESS STEEL IN FUMING NITRIC ACID AT 170° F. 
Charles E. Feiler and Gerald Morrell. February 
1954. 22p. diagrs., photos., tabs. 
(NACA RM E53L17b) 



FLAME PROPAGATION LIMITS OF PROPANE AND 
n-PENTANE IN OXIDES OF NITROGEN. Riley O. 
Miller. August 1955. 29p. diagrs., 3 tabs. (NACA 
TN 3520) 



EXPERIMENTAL AND CALCULATED TEMPERA- 
TURE AND MASS HISTORIES OF VAPORIZING 
FUEL DROPS. M. M. El Wakil, R. J. Priem, 
H. J. Brikowski, P. S. Myers, and O. A. Uyehara, 
Wisconsin University. January 1956. 82p. diagrs., 
photos ., tab (NACA TN 3490) 



THEORETICAL PERFORMANCE OF JP-4 FUEL 
AND LIQUID OXYGEN AS A ROCKET PROPEL- 
LANT. I - FROZEN COMPOSITION. Vearl N. Huff 
and Anthony Fortini. April 1956. 35p. diagrs., 
tabs. (NACA RM E56A27) 



136 



(3) PROPULSION 



(3.5) 
Combustion and Combustors 



AN INVESTIGATION OF HIGH-FREQUENCY COM- 
BUSTION OSCILLATIONS IN LIQUID-PROPELLANT 
ROCKET ENGINES. Adelbert O. Tischler, Rudolph 
V. Massa and Raymond L. Mantler. June 1953. 
37p. diagrs., photos. (NACA RM E53B27) 



A POLAR-COORDINATE SURVEY METHOD FOR 
DETERMINING JET-ENGINE COMBUSTION- 
CHAMBER PERFORMANCE. Robert Friedman and 
Edward R. Carlson. September 1955. 29p. 
diagrs., photo., tab. (NACA TN 3566) 



STUDY OF SCREECHING COMBUSTION IN A 
6-INCH SIMULATED AFTERBURNER. Perry L. 
Blackshear, Warren D. Rayle, and Leonard K. 
Tower. October 1955. 58p. diagrs., photos., tab. 
(NACA TN 3567) 



DISCHARGE COEFFICIENTS FOR COMBUSTOR- 
LINER AIR-ENTRY HOLES. I - CIRCULAR HOLES 
WITH PARALLEL FLOW. Ralph T. Dittrich and 
Charles C. Graves. April 1956. 39p. diagrs. 
(NACA TN 3663) 



STABILITY OF SYSTEMS CONTAINING A HEAT 
SOURCE - THE RAYLEIGH CRITERION. Boa-Teh 
Chu f Johns Hopkins University. June 1956. 25p. 
diagrs. (NACA RM 56D27) 



(3.5.1) 

GENERAL COMBUSTION 

RESEARCH 

PERFORMANCE OF A RAM-JET-TYPE COM- 

BUSTOR WITH FLAME HOLDERS IMMERSED IN 
THE COMBUSTION ZONE. Roland Breitwieser. 
November 1, 1948. 47p. diagrs., photos. 
(NACA RM E8F21) 



FLAME VELOCITIES OF FOUR ALKYLSILANES. 
Melvin Gerstein, Edgar L. Wong, and Oscar Levine. 
March 9, 1951. 14p. diagrs., tab. 
(NACA RM E51A08) 



PRELIMINARY EVALUATION OF THE AIR AND 
FUEL SPECIFIC-IMPULSE CHARACTERISTICS OF 
SEVERAL POTENTIAL RAM-JET FUELS. I - 
OCTENE-1, ALUMINUM, AJSiD ALUMINUM - 
OCTENE-1 SLURRIES. Benson E. Gammon. 
April 30. 1951. 20p. diagr.s. (NACA RM E51C12) 



PRELIMINARY EVALUATION OF THE AIR AND 
FUEL SPECIFIC-IMPULSE CHARACTERISTICS OF 
SEVERAL POTENTIAL RAM-JET FUELS. II - 
MAGNESIUM AND MAGNESIUM - OCTENE-1 
SLURRIES. Benson E. Gammon. May 2, 1951. 
15p. diagrs. (NACA RM E51C23) 



PRELIMINARY EVALUATION OF THE AIR AND 
FUEL SPECIFIC-IMPULSE CHARACTERISTICS OF 
SEVERAL POTENTIAL RAM- JET FUELS. HI - 
DIBORANE, PENTABORANE, BORON, AND BORON- 
OCTENE-1 SLURRIES. Benson E. Gammon. July 
1951. 26p. diagrs. (NACA RM E51D25) 



PRELIMINARY EVALUATION OF THE AIR AND 
FUEL SPECIFIC -IMPULSE CHARACTERISTICS OF 
SEVERAL POTENTIAL RAM-JET FUELS. IV - 
HYDROGEN, a-METHYLNAPHTHALENE, AND 
CARBON. Benson E. Gammon. August 1951. 22p. 
diagrs. (NACA RM E51F05) 



IGNITION -DELAY CHARACTERISTICS IN MODIFIED 
OPEN-CUP APPARATUS OF SEVERAL FUELS 
WITH NITRIC ACID OXIDANTS WITHIN TEMPERA- 
TURE RANGE 70° TO -105° F. Riley O. Miller. 
December 1951. 30p. diagrs., 4 tabs. 
(NACA RM E51J11) 



EFFECT OF SPARK REPETITION RATE ON THE 
IGNITION LIMITS OF A SINGLE TUBULAR COM- 
BUSTOR. Hampton H. Foster. December 1951. 
12p. diagrs., tab. (NACA RM E51J18) 



EFFECT OF INLET -AIR AND FUEL PARAMETERS 
ON SMOKING CHARACTERISTICS OF A SINGLE 
TUBULAR TURBOJET -ENGINE COMBUSTOR. 
Helmut F. Butze. April 1952. 26p. diagrs.. 
photos ., tabs. (NACA RM E52A18) 



EFFECT OF OXYGEN CONCENTRATION OF THE 
INLET OXYGEN-NITROGEN MDCTURE ON THE 
COMBUSTION EFFICIENCY OF A SINGLE J33 
TURBOJET COMBUSTOR. Charles C. Graves. 
August 1952, 45p. diagrs., 2 tabs. 
(NACA RM E52F13) 



SUMMARY REPORT ON ANALYTICAL EVALUATION 
OF AIR AND FUEL SPECIFIC -IMPULSE CHARAC- 
TERISTICS OF SEVERAL NONHYDROCARBON JET- 
ENGINE FUELS. Roland Breitwieser, Sanford 
Gordon and Benson Gammon. February 1953. 
58p. diagrs., tab. (NACA RM E52L08) 



EFFECT OF INLET OXYGEN CONCENTRATION ON 
COMBUSTION EFFICIENCY OF J33 SINGLE COM- 
BUSTOR OPERATING WITH GASEOUS PROPANE. 
Charles C. Graves. March 1953. 22p. diagrs., 
tab. (NACA RM E53A27) 

AN INVESTIGATION OF HIGH-FREQUENCY COM- 
BUSTION OSCILLATIONS IN LIQUID-PROPELLANT 
ROCKET ENGINES. Adelbert O. Tischler, Rudolph 
V. Massa and Raymond L. Mantler. June 1953. 
37p. diagrs., photos. (NACA RM E53B27) 



EFFECTS OF NITROGEN TETROXIDE AND WATER 
CONCENTRATION ON FREEZING POINT AND IGNI- 
TION DELAY OF FUMING NITRIC ACID. Riley O. 
Miller. September 1953. 32p. diagrs., tabs. 
(NACA RM E53G31) 



137 



(3) PROPULSION 



PROPAGATION OF A FREE FLAME IN A TURBU- 
LENT GAS STREAM. William R. Mickelsen and 
Norman E. Ernstein. July 1955. 89p. diagrs 
photos., 2 tabs. (NACA TN 3456) 



IDEAL TEMPERATURE RISE DUE TO CONSTANT - 
PRESSURE COMBUSTION OF A JP-4 FUEL 
S(idney) C. Huntley. September 1955. 53p! 
diagrs., tabs. (NACA RM E55G27a) 



CHEMICAL ACTION OF HALOGENATED AGENTS 
IN FIRE EXTINGUISHING. Frank E. Belles 
September 1955. 28p. diagrs., 3 tabs. (NACA 
TN 3565) 



AN EXPERIMENTAL COMPARISON OF THE 
LAGRANGIAN AND EULERIAN CORRELATION 
COEFFICIENTS IN HOMOGENEOUS ISOTROPIC 
TURBULENCE. William R. Mickelsen. October 
1955. 42p. diagrs. (NACA TN 3570) 



STABILITY OF SYSTEMS CONTAINING A HEAT 
SOURCE - THE RAYLEIGH CRITERION. Boa- Teh 
Chu, Johns Hopkins University. June 1956 25d 
diagrs. (NACA RM 56D27) 



SPACE HEATING RATES FOR SOME PREMIXED 
TURBULENT PROPANE-AIR FLAMES. Burton D. 
Fine and Paul Wagner. June 1956. 26p. diagrs. 
tab. (NACA TN 3277) ' 



(3.5. 1.1) 
LAMINAR-FLOW COMBUSTION 



CHEMICAL ACTION OF HALOGENATED AGENTS 
IN FIRE EXTINGUISHING. Frank E. Belles. 
September 1955. 28p. diagrs., 3 tabs. (NACA 
TN 3565) 



BURNING VELOCITIES OF VARIOUS PREMDCED 
TURBULENT PROPANE FLAMES ON OPEN 
BURNERS. Paul Wagner. October 1955. 32p. 
diagrs., photos., tab. (NACA TN 3575) 



(3. 5. 1.2) 
TURBULENT-FLOW COMBUSTION 

COMBUSTION EFFICIENCY OF HOMOGENEOUS 
FUEL-AIR MIXTURES IN A 5-INCH RAM-JET- 
TYPE COMBUSTOR, Thaine W. Reynolds and 
Robert D. Ingebo. November 1952. 36p. diagrs. 
tabs. (NACA RM E52I23) 



EFFECT OF FUELS ON COMBUSTION EFFICIENCY 
OF 5-INCH RAM-JET-TYPE COMBUSTION. 
Thaine W. Reynolds. May 1953. 40p. diagrs., 
tabs. (NACA RM E53C20) 



PROPAGATION OF A FREE FLAME IN A TURBU- 
LENT GAS STREAM. William R. Mickelsen and 
Norman E. Ernstein. July 1955. 89p. diagrs 
photos., 2 tabs. (NACA TN 3456> 



BURNING VELOCITIES OF VARIOUS PREMLXED 
TURBULENT PROPANE FLAMES ON OPEN 
BURNERS. Paul Wagner. October 1955. 32p. 
diagrs., photos., tab. (NACA TN 3575) 



STABILITY OF SYSTEMS CONTAINING A HEAT 
SOURCE - THE RAYLEIGH CRITERION. Boa- Teh 
Chu, Johns Hopkins University. June 1956. 25p 
diagrs. (NACA RM 56D27) 



SPACE HEATING RATES FOR SOME PREMIXED 
TURBULENT PROPANE-AIR FLAMES. Burton D. 
Fine and Paul Wagner. June 1956. 26p. diagrs 
tab (NACA TN 3277) ' 



(3. 5. 1.4) 
EFFECTS OF FUEL ATOMIZATION 



EXPERIMENTAL AND CALCULATED TEMPERA- 
TURE AND MASS HISTORIES OF VAPORIZING 
FUEL DROPS. M M. El Wakil, R. J. Priem, 
H. J. Brikowski, P. S. Myers, and O. A. Uyehara, 
Wisconsin University. January 1956. 82p diagrs* 
photos., tab. (NACA TN 3490) 



(3. 5. 1. 5) 
REACTION MECHANISMS 



EFFECT OF OXYGEN CONCENTRATION OF THE 
INLET OXYGEN-NITROGEN MIXTURE ON THE 
COMBUSTION EFFICIENCY OF A SINGLE J33 
TURBOJET COMBUSTOR. Charles C. Graves 
August 1952. 45p. diagrs., 2 tabs. 
(NACA RM E52F13) 



EFFECT OF INLET OXYGEN CONCENTRATION ON 
COMBUSTION EFFICIENCY OF J33 SINGLE COM- 
BUSTOR OPERATING WITH GASEOUS PROPANE. 
Charles C. Graves. March 1953. 22p. diaers 
tab. (NACA RM E53A27) "' 



EFFECT OF HYDROCARBON STRUCTURE ON 
REACTION PROCESSES LEADING TO SPONTANE- 
OUS IGNITION. Donald E. Swarts and Charles E. 
Frank, University of Cincinnati. July 1955. 23p 
diagrs., 6 tabs. (NACA TN 3384) 



VAPOR- PHASE OXIDATION AND SPONTANEOUS 
IGNITION - CORRELATION AND EFFECT OF VARI- 
ABLES. Donald E. Swarts and Milton Or chin, 
University of Cincinnati. April 1956. 32p. diaers 
tabs. (NACA TN 3579) ' 



138 



(3) PROPULSION 



(3.5. 1.6) 
IGNITION OF GASES 



FLAME PROPAGATION LIMITS OF PROPANE AND 
n-PENTANE IN OXIDES OF NITROGEN. Riley O. 
Miller. August 1955. 29p. diagrs., 3 tabs. (NACA 
TN 3520) 



CHEMICAL ACTION OF HALOGENATED AGENTS 
IN FIRE EXTINGUISHING. Frank E. Belles. 
September 1955. 28p. diagrs., 3 tabs. (NACA 
TN 3565) 



SPARK IGNITION OF FLOWING GASES. V - AP- 
PLICATION OF FUEL -AIR- RATIO AND INITIAL- 
TEMPERATURE DATA TO IGNITION THEORY. 
Clyde C. Swett, Jr. November 1955. 19p. diagrs. 
(NACA RM E55I16) 



VAPOR-PHASE OXIDATION AND SPONTANEOUS 
IGNITION - CORRELATION AND EFFECT OF VARI- 
ABLES. Donald E. S warts and Milton Or chin, 
University of Cincinnati. April 1956. 32p. diagrs., 
tabs. (NACA TN 3579) 



(3.5.2) 
EFFECT OF ENGINE OPERATING 
CONDITIONS AND COMBUSTION 
CHAMBER GEOMETRY 

PERFORMANCE OF A 20-INCH STEADY-FLOW 
RAM JET AT HIGH ALTITUDES AND RAM- 
PRESSURE RATIOS. Eugene Perchonok, William H. 
Sterbentz, and Fred A. Wilcox. June 25, 1947. 39p. 
diagrs.. photos. (NACA RM E6L06) 



SOME EFFECTS OF GUTTER FLAME-HOLDER 
DIMENSIONS ON COMBUSTION-CHAMBER PER- 
FORMANCE OF 20 -INCH RAM JET. Fred A. 
Wilcox, Eugene Perchonok, and George Wishnek. 
July 30, 1948. 39p. diagrs., photos., tab. 
(NACA RM E8C22) 



INVESTIGATION OF INTERNAL REGENERATIVE 
FUEL-HEATING SYSTEM FOR 20-INCH RAM JET. 
Sol Baker and Eugene Perchonok. September 1, 
1949. 22p. diagrs., photos. (NACA RM E9F20) 



EFFECT OF INLET-AIR AND FUEL PARAMETERS 
ON SMOKING CHARACTERISTICS OF A SINGLE 
TUBULAR TURBOJET-ENGINE COMBUSTOR 

Helmut F. Butze. April 1952. 26p. diagrs.. 
photos., tabs. (NACA RM E52A18) 



EFFECT OF OXYGEN CONCENTRATION OF THE 
INLET OXYGEN-NITROGEN MIXTURE ON THE 
COMBUSTION EFFICIENCY OF A SINGLE J33 
TURBOJET COMBUSTOR. Charles C. Graves. 
August 1952. 45p. diagrs., 2 tabs. 
(NACA RM E52F13) 



EFFECT OF INLET OXYGEN CONCENTRATION ON 
COMBUSTION EFFICIENCY OF J33 SINGLE COM- 
BUSTOR OPERATING WITH GASEOUS PROPANE. 
Charles C. Graves. March 1953. 22p. diagrs., 
tab. (NACA RM E53A27) 



AN INVESTIGATION OF HIGH-FREQUENCY COM- 
BUSTION OSCILLATIONS IN LIQUID -PROPELLANT 
ROCKET ENGINES. Adelbert O. Tischler, Rudolph 
V. Massa and Raymond L. Mantler. June 1953. 
37p. diagrs., photos. (NACA RM E53B27) 



ANALYTICAL EVALUATION OF EFFECT OF 
EQUIVALENCE RATIO, INLET-AIR TEMPERA- 
TURE, AND COMBUSTION PRESSURE ON PER- 
FORMANCE OF SEVERAL POSSIBLE RAM-JET 
FUELS. Leonard K. Tower and Benson E. Gammon. 
September 1953. 59p. diagrs., tabs. 
(NACA RM E53G14) 



INVESTIGATION OF A PULSE-JET-POWERED 
HELICOPTER ROTOR ON THE LANGLEY HELI- 
COPTER TEST TOWER. Edward J. Radin and 
Paul J. Carpenter. February 1954. 23p. diagrs., 
photos. (NACA RM L53L15) 



AN EXPERIMENTAL COMPARISON OF THE 
LAGRANGIAN AND EULERIAN CORRELATION 
COEFFICIENTS IN HOMOGENEOUS ISOTROPIC 
TURBULENCE. William R. Mickelsen. October 
1955. 42p. diagrs. (NACA TN 3570) 



INVESTIGATION OF THE PROPULSIVE CHARAC- 
TERISTICS OF A HELICOPTER-TYPE PULSE-JET 
ENGINE OVER A RANGE OF MACH NUMBERS AND 
ANGLE OF YAW. Paul J. Carpenter, James P. 
Shivers, and Edwin E. Lee, Jr. January 1956. 
24p. diagrs., photos. (NACA TN 3625) 



(3.5.2.2) 
TURBINE ENGINES 



PERFORMANCE INVESTIGATION OF CAN-TYPE 
COMBUSTOR. II - WATER INJECTION AT VARI- 
OUS STATIONS IN COMBUSTOR. William P. Cook 
and Eugene V. Zettle. September 30, 1948. 27p. 
diagrs. (NACA RM E8F28) 



PRELIMINARY CORRELATION OF EFFICIENCY OF 
AIRCRAFT GAS-TURBINE COMBUSTORS FOR 
DIFFERENT OPERATING CONDITIONS. J. Howard 
Childs. September 21, 1950. 40p. diagrs., tab. 
(NACA RM E50F15) 



EFFECT OF SPARK REPETITION RATE ON THE 
IGNITION LIMITS OF A SINGLE TUBULAR COM- 
BUSTOR. Hampton H. Foster. December 1951. 
12p. diagrs., tab. (NACA RM E51J18) 



EFFECT OF INLET-AIR AND FUEL PARAMETERS 
ON SMOKING CHARACTERISTICS OF A SINGLE 
TUBULAR TURBOJET-ENGINE COMBUSTOR 
Helmut F. Butze. April 1952. 26p. diagrs.. 
photos., tabs. (NACA RM E52A18) 



139 



(3) PROPULSION 



ANALYTICAL EVALUATION OF EFFECT OF 
EQUIVALENCE RATIO, INLET-AIR TEMPERA- 
TURE, AND COMBUSTION PRESSURE ON PER- 
FORMANCE OF SEVERAL POSSIBLE RAM-JET 
FUELS. Leonard K. Tower and Benson K. Gammon. 
September 1953. 59p. diagrs., tabs. 
(NACA RM E53G14) 



RELATION OF TURBINE-ENGINE COMBUSTION 
EFFICIENCY TO SECOND-ORDER REACTION 
KINETICS AND FUNDAMENTAL FLAME SPEED. 
J. Howard Childs and Charles C. Graves. August 
1954. 37p. diagrs. (NACA RM E54G23) 



ideal temperature rise due to constant - 
Pressure combustion of a jp-4 fuel. 

S(idney) C. Huntley. September 1955. 53p. 
diagrs., tabs. (NACA RM E55G27a) 



A POLAR-COORDINATE SURVEY METHOD FOR 
DETERMINING JET -ENGINE COMBUSTION- 
CHAMBER PERFORMANCE. Robert Friedman and 
Edward R. Carlson. September 1955. 29p. 
diagrs., photo., tab. (NACA TN 3566) 



(3. 5, 2 S 3) 
RAM -JET ENGINES 



FLIGHT INVESTIGATION OF A 20-INCH-DIAMETER 
STEADY-FLOW RAM JET. John H. Disher. 
January 14, 1948. 29p. diagrs., photo. 
(NACA RM E7I0jd) 



INVESTIGATION OF EFFECTS OF MOVABLE 
EXHAUST-NOZZLE PLUG ON OPERATIONAL PER- 
FORMANCE OF 20-INCH RAM JET. William H. 
Sterbentz and Fred A. Wilcox. July 27, 1948. 32p. 
diagrs., photos. (NACA RM E8D22) 



SOME EFFECTS OF GUTTER FLAME-HOLDER 
DIMENSIONS ON COMBUSTION-CHAMBER PER- 
FORMANCE OF 20-INCH RAM JET. Fred A. 
Wilcox, Eugene Perchonok, and George Wishnek. 
July 30, 1948. 39p. diagrs., photos., tab. 
(NACA RM E8C22) 

PRELIMINARY INVESTIGATION OF EFFECTS OF 
COMBUSTION IN RAM JET ON PERFORMANCE OF 
SUPERSONIC DIFFUSERS. I - SHOCK DIFFUSER 
WITH TRIPLE-SHOCK PROJECTING CONE. J. F. 

Connors and A. H. Schroeder. September 15, 1948. 
18p. diagrs. (NACA RM E8F15) 

PRELIMINARY INVESTIGATION OF EFFECTS OF 
COMBUSTION IN RAM JET ON PERFORMANCE OF 
SUPERSONIC DIFFUSERS. II - PERFORATED 
SUPERSONIC INLET. Albert H. Schroeder and 
James F. Connors. October 4, 1948. 14p. diagrs. 
(NACA RME8G16) 

PERFORMANCE OF A RAM-JET-TYPE COM- 
BUSTOR WITH FLAME HOLDERS IMMERSED IN 
THE COMBUSTION ZONE. Roland Breitwieser. 
November 1, 1948. 47p. diagrs., photos. 
(NACA RM E8F21) 



EFFECT OF THREE FLAME-HOLDER CONFIGU- 
RATIONS ON SUBSONIC FLIGHT PERFORMANCE 
OF RECTANGULAR RAM JET OVER RANGE OF 
ALTITUDES. Dugald O. Black and Wesley E. 
Messing. November 24, 1948, 28p. diagrs., photo., 
tab. (NACA RM E8I01) 



EFFECT OF VARIATION IN FUEL PRESSURE ON 
COMBUSTION PERFORMANCE OF RECTANGULAR 
RAMJET. Wesley E. Messing and Dugald O. Black. 
November 24, 1948. 26p. diagrs., photo., tab. 
(NACA RM E8I28) 



PRELIMINARY INVESTIGATION OF EFFECTS OF 
COMBUSTION IN RAM JET ON PERFORMANCE OF 
SUPERSONIC DIFFUSERS. Ill - NORMAL-SHOCK 
DIFFUSER. Albert H. Schroeder and James F. 
Connors. December 22, 1948. 15p. diagrs. 
(NACARME8J18) 



DESIGN FACTORS FOR 4- BY 8-INCH RAM -JET 
COMBUSTOR. Donald W. Male and Adolph J. 
Cervenka. August 11, 1949. 47p. diagrs., photos. 
(NACARM E9F09) 



FREE-FLIGHT PERFORMANCE OF 16-INCH- 
DIAMETER SUPERSONIC RAM-JET UNITS. I - 
FOUR UNITS DESIGNED FOR COMBUSTION - 
CHAMBER-INLET MACH NUMBER OF 0.12 AT 
FREE-STREAM MACH NTIMBER OF 1.6 (UNITS A-2. 
A-3, A-4, AND A-5). William W. Carlton and 
Wesley E. Messing. September 22, 1949. 51p. 
diagrs.. photos. (NACA RM E9F22) 



EXPERIMENTAL INVESTIGATION OF PRESSURE 
FLUCTUATIONS IN 3.6-INCH RAM JET AT MACH 
NUMBER 1.92. James F. Connors and Albert II. 
Schroeder. October 13, 1949. 20p. diagrs., photos. 
(NACARM E9H12) 



PRELIMINARY INVESTIGATION OF HELMHOLTZ 
RESONATORS FOR DAMPING PRESSURE FLUCTU- 
ATIONS IN 3. 6 -INCH RAM JET AT MACH NUMBER 
1.90. Jerome L. Fox. May 22, 1951. 24p. diagrs., 
photos. (NACA RM E51C05) 



ANALYTICAL INVESTIGATION OF RAM-JET EN- 
GINE PERFORMANCE IN FLIGHT MACH NUMBER 
RANGE FROM 3 TO 7. Philip J. Evans, Jr. 
October 1951. 29p. diagrs. (NACA RM E51H02) 



EFFECT OF FUEL-AIR DISTRIBUTION ON PER- 
FORMANCE OF A 16-INCH RAM-JET ENGINE. 
A. J. Cervenka and E. E. Dangle. June 1952. 
25p. diagrs., photos., tab. (NACA RM E52D08) 



COMBUSTION EFFICIENCY OF HOMOGENEOUS 
FUEL-AIR MIXTURES IN A 5-INCH RAM-JET- 
TYPE COMBUSTOR. Thaine W. Reynolds and 
Robert D. Ingebo. November 1952. 36p. diagrs., 
tabs. (NACA RM E52I23) 



EFFECT OF FUELS ON COMBUSTION EFFICIENCY 
OF 5-INCH RAM-JET-TYPE COMBUSTION. 
Thaine W. Reynolds. May 1953. 40p. diagrs., 

tabs. (NACA RM E53C20) 



140 



(3) PROPULSION 



ANALYTICAL EVALUATION OF EFFECT OF 
EQUIVALENCE RATIO. IN LET- AIR TEMPERA- 
TURE, AND COMBUSTION PRESSURE ON PER- 
FORMANCE OF SEVERAL POSSIBLE RAM-JET 
FUELS. Leonard K. Tower and Benson E. Gammon. 
September 1953. 59p. diagrs., tabs. 
(NACA RM E53G14) 



IDEAL TEMPERATURE RISE DUE TO CONSTANT - 
PRESSURE COMBUSTION OF A JP-4 FUEL. 

S(idney) C. Huntley. September 1955. 53p. 
diagrs., tabs. (NACA RM E55G27a) 



EVAPORATION OF JP-5 FUEL SPRAYS IN AIR 
STREAMS. Hampton H. Foster and Robert D. 
Ingebo. February 1956. 26p. diagrs., tabs. 
(NACA RM E55K02) 



(3. 5.2. 5) 
ROCKET ENGINES 



THEORETICAL PERFORMANCE OF SOME ROCKET 
PROPELLANTS CONTAINING HYDROGEN, 
NITROGEN, AND OXYGEN. Riley O. Miller and 
Paul M. Ordin. May 26. 1948. 53p. diagrs., tabs. 
{NACA RM E8A30) 



STARTING OF ROCKET ENGINE AT CONDITIONS 
OF SIMULATED ALTITUDE USING CRUDE MONO- 
ETHYLANILINE AND OTHER FUELS WITH MLXED 
ACID. Dezso J. Ladanyi, John L. Sloop, Jack C. 
Humphrey, and Gerald Morrell. July 19, 1950. 
64p. diagrs., photos., tabs. (NACA RM E50D20) 



IGNITION -DELAY CHARACTERISTICS IN MODIFIED 
OPEN-CUP APPARATUS OF SEVERAL FUELS 
WITH NITRIC ACID OXIDANTS WITHIN TEMPERA- 
TURE RANGE 70° TO -105° F. Riley O. Miller. 
December 1951. 30p. diagrs., 4 tabs. 
(NACA RME51J11) 



IGNITION DELAY EXPERIMENTS WITH SMALL- 
SCALE ROCKET ENGINE AT SIMULATED ALTI- 
TUDE CONDITIONS USING VARIOUS FUELS WITH 
NITRIC ACID OXIDANTS. Dezso J. Ladanyi. 
January 1952. 44p. diagrs., photos., tabs. 
(NACA RM E51J01) 



ORTHOTOLUIDINE AND TRIETHYLAMINE IN 
ROCKET ENGINE APPLICATIONS. Dezso J. 
Ladanyi. January 1953. 24p. diagrs., tabs. 
(NACA RM E52K19) 



AN INVESTIGATION OF HIGH-FREQUENCY COM- 
BUSTION OSCILLATIONS IRLIQUID-PROPELLANT 
ROCKET ENGINES. Adelbert O. Tischler, Rudolph 
V. Massa and Raymond L. Mantler. June 1953. 
37p. diagrs., photos. (NACA RM E53B27) 



COMPARISON OF IGNITION DELAYS OF SEVERAL 
PROPEL LAN T COMBINATIONS OBTAINED WITH 
MODIFIED OPEN-CUP AND SMALL-SCALE ROCK- 
ET ENGINE APPARATUS. Dezso J. Ladanyi and 
Riley O. Miller. June 1953. 20p. diagrs., photos., 
tabs. (NACA RM E53D03) 



EFFECTS OF NITROGEN TETROXIDE AND WATER 
CONCENTRATION ON FREEZING POINT AND IGNI- 
TION DELAY OF FUMING NITRIC ACID. Riley O. 
Miller. September 1953. 32p. diagrs., tabs. 
(NACA RM E53G31) 



INVESTIGATION OF EFFECT OF FLUORIDE ON 
CORROSION OF 2S-0 ALUMINUM AND 347 STAIN- 
LESS STEEL IN FUMING NITRIC ACID AT 170° F. 
Charles E. Feller and Gerald Morrell. February 
1954. 22p. diagrs., photos., tabs. 
(NACA RM E53L17b) 



FLAME PROPAGATION LIMITS OF PROPANE AND 
n-PENTANE IN OXIDES OF NITROGEN. Riley O. 
Miller. August 1955. 29p. diagrs., 3 tabs. (NACA 
TN 3520) 



THEORETICAL PERFORMANCE OF JP-4 FUEL 
AND LIQUID OXYGEN AS A ROCKET PROPEL- 
LANT. I - FROZEN COMPOSITION. Vearl N. Huff 
and Anthony Fortini. April 1956. 35p. diagrs., 
tabs. (NACA RM E56A27) 



141 



(3) PROPULSION 



(3.6) 
Compression and Compressors 



DESIGN AND TEST OF MDCED-FLOW IMPELLERS 
I - AERODYNAMIC DESIGN PROCEDURE. 
Walter M. Osborn and Joseph T. Hamrick. 
September 1952. 42p. diagrs., photo., tab. 
(NACA RM E52E05) 



DESIGN AND TEST OF MDCED-FLOW IMPELLERS. 
II - EXPERIMENTAL RESULTS, IMPELLER 
MODEL MFI-1A. Joseph R. Withee, Jr., and 
William L. Beede. September 1952. 28p. diagrs., 
photos., tab. {NACA RM E52E22) 



SOME EFFECTS OF GUIDE-VANE TURNING AND 
STATORS ON THE ROTATING STALL CHARACTER- 
ISTICS OF A HIGH HUB-TIP RATIO SINGLE-STAGE 
COMPRESSOR. Eleanor L. Costilow and Merle C. 
Huppert. April 1956. 52p. diagrs., tab. 
(NACA TN3711) 



(3.6.1) 

FLOW THEORY AND 

EXPERIMENT 



PRELIMINARY INVESTIGATION OF FLOW FLUC- 
TUATIONS DURING SURGE AND BLADE ROW 
STALL IN AXIAL-FLOW COMPRESSORS. Merle C. 
Huppert. August 1952. 52p. diagrs., photos. 
(NACA RM E52E28) 



DESIGN AND TEST OF MDCED-FLOW IMPELLERS. 
II - EXPERIMENTAL RESULTS, IMPELLER 
MODEL MFI-1A. Joseph R. Withee, Jr., and 
William L. Beede. September 1952. 28p. diagrs., 
photos., tab. (NACA RM E52E22) 



PRELIMINARY INVESTIGATION OF COMPRESSOR 
BLADE VIBRATION EXCITED BY ROTATING 
STALL. Merle C. Huppert, Donald F. Johnson, and 
Eleanor L. Costilow. December 1952. 27p. diagrs., 
photos, (NACA RM E52J15) 



EXPERIMENTAL AND THEORETICAL INVESTIGA- 
TION OF ROTATING-STALL CHARACTERISTICS OF 
SINGLE-STAGE AXIAL-FLOW COMPRESSOR WITH 
HUB-TIP RATIO OF 0.76. Robert W. Graham and 
Vasily D. Prian, November 1653. 34p. diagrs., 
photos., tab. (NACA RM E53I09) 



TWO-DIMENSIONAL LOW -SPEED CASCADE INVES- 
TIGATION OF NACA COMPRESSOR BLADE SEC- 
TIONS HAVING A SYSTEMATIC VARIATION IN 
MEAN-LINE LOADING. John R. Erwin, Melvyn 
Savage, and James C. Emery. November 1953. 
129p. diagrs., tabs. (NACA RM L53I30b) 



METHOD OF ESTIMATING THE INCOMPRESSIBLE- 
FLOW PRESSURE DISTRIBUTION OF COMPRESSOR 
BLADE SECTIONS AT DESIGN ANGLE OF ATTACK. 
John R. Erwin and Laura A. Yacobi. December 
1953. 41p. diagrs., tab. (NACA RM L53F17) 



APPROXIMATE METHOD FOR DETERMINING 
EQUILIBRIUM OPERATION OF COMPRESSOR 
COMPONENT OF TURBOJET ENGINE. Merle C. 
Huppert. July 1955. 25p. diagrs. (NACA TN 3517) 



ROTATING-STALL CHARACTERISTICS OF A 
ROTOR WITH HIGH HUB-TIP RADIUS RATIO. 
Eleanor L. Costilow and Merle C. Huppert. August 
1955. 59p. diagrs., photos. (NACA TN 3518) 



A SURVEY OF UNCLASSIFIED AXIAL-FLOW- 
COMPRESSOR LITERATURE. Howard Z. Herzig 
and Arthur G. Hansen. November 1955. i, 88p. 
(NACARM E55H11) 



LIFT HYSTERESIS AT STALL AS AN UNSTEADY 
BOUNDARY-LAYER PHENOMENON. Franklin K. 
Moore. November 1955. 32p. diagrs., tab. 
(NACA TN 3571) 



FLOW OF GAS THROUGH TURBINE LATTICES. 
M. E. Deich. May 1956. 136p. diagrs., photos. 
(NACA TM 1393. Trans, of Russian book: 
Technical Gasdynamics, ch. 7, 1953, p. 312-420) 



(3.6. 1. 1) 
AXIAL FLOW 



EXPERIMENTAL INVESTIGATION OF THRUST 
AUGMENTATION OF 4000-POUND-THRUST AXIAL- 
FLOW-TYPE TURBOJET ENGINE BY INTERSTAGE 
INJECTION OF WATER-ALCOHOL MTXTURES IN 
COMPRESSOR. John H. Povolny, James W. Useller, 
and Louis J. Chelko. April 6, 1950. 42p. diagrs., 
photos., tab. (NACA RM E9K30) 



ALTITUDE INVESTIGATION OF PERFORMANCE OF 
TURBINE-PROPELLER ENGINE AND ITS COMPO- 
NENTS. Lewis E. Wallner and Martin J. Saari. 
October 5, 1950. 65p. diagrs., photos. (NACA 
RM E50H30) 



SYSTEMATIC TWO-DIMENSIONAL CASCADE TESTS 
OF NACA 65-SERIES COMPRESSOR BLADES AT 
LOW SPEEDS. L. Joseph Herrig, James C. Emery, 
and John R. Erwin. September 1951. 223p. 
diagrs., photo., tabs. (NACA RM L51G31) 



142 



(3) PROPULSION 



SOME EFFECTS OF BLADE TRAILING-EDGE 
THICKNESS ON PERFORMANCE OF A SINGLE- 
STAGE AXIAL-FLOW COMPRESSOR. J. J- Moses 
andG. K. Serovy. October 1951. Up. diagrs., tab. 

(NACARME51F28) 



COMPARISON OF NACA 65-SERIES COMPRESSOR- 
BLADE PRESSURE DISTRIBUTIONS AND PER- 
FORMANCE IN A ROTOR AND IN CASCADE. 
Willard R. Westphal and William R. Godwin. 
November 1951. 53p. diagrs,, photos. 
(NACA RM L51H20) 



EFFECT OF SECTION THICKNESS AND TRAILING- 
EDGE RADIUS ON THE PERFORMANCE OF NACA 
65-SERIES COMPRESSOR BLADES IN CASCADE AT 
LOW SPEEDS. L. Joseph Herrig, James C. Emery, 
and John R. Erwin. December 1951. 66p. diagrs., 
tabs. (NACA RM L51J16) 



PRELIMINARY INVESTIGATION OF COMPRESSOR 
BLADE VIBRATION EXCITED BY ROTATING 
STALL. Merle C Huppert, Donald F. Johnson, and 
Eleanor L. Costilow. December 1952. 27p. diagrs., 
photos. (NACA RM E52J15) 



INTERSTAGE SURVEYS AND ANALYSIS OF VIS- 
COUS ACTION IN LATTER STAGES OF A MULTI- 
STAGE AXIAL-FLOW COMPRESSOR. William B, 
Briggs and Charles C. Giamati. March 1953. 51p. 

diagrs., phuto., tab. (NACA RM E52I12) 



A COMPARISON OF TYPICAL NATIONAL GAS TUR- 
BINE ESTABLISHMENT AND NACA AXIAL -FLOW 
COMPRESSOR BLADE SECTIONS IN CASCADE AT 
LOW SPEED. A. Richard Felix and James C. 
Emery. May 1953. 46p. diagrs., photo., tabs. 
(NACA RM L53B26a) 



EXPERIMENTAL AND THEORETICAL INVESTIGA- 
TION OF ROTATING-STALL CHARACTERISTICS OF 
SINGLE-STAGE AXIAL-FLOW COMPRESSOR WITH 
HUB-TIP RATIO OF 0.76. Robert W. Graham and 
Vasily D. Prian. November 1S53. 34p. diagrs., 
photos., tab. (NACA RM E53I09) 



TWO-DIMENSIONAL LOW -SPEED CASCADE INVES- 
TIGATION OF NACA COMPRESSOR BLADE SEC- 
TIONS HAVING A SYSTEMATIC VARIATION IN 
MEAN-LINE LOADING. John R. Erwin, Melvyn 
Savage, and James C. Emery. November 1953. 
129p. diagrs., tabs. (NACA RM L53I30b) 



SUMMARY OF 65-SERIES COMPRESSOR-BLADE 
LOW-SPEED CASCADE DATA BY USE OF THE 
CARPET-PLOTTING TECHNIQUE. A. Richard 
Felix. November 1954. 9p. diagrs. 
(NACA RM L54H18a) 



ANALYSIS OF TWO-DIMENSIONAL COMPRESSIBLE- 
FLOW LOSS CHARACTERISTICS DOWNSTREAM OF 
TURBOMACHINE BLADE ROWS IN TERMS OF 
BASIC BOUNDARY-LAYER CHARACTERISTICS. 
Warner L. Stewart. July 1955. 48p. diagrs. (NACA 
TN3515) 



APPROXIMATE METHOD FOR DETERMINING 
EQUILIBRIUM OPERATION OF COMPRESSOR 
COMPONENT OF TURBOJET ENGINE. Merle C. 
Huppert. July 1955. 25p. diagrs. (NACA TN 3517) 



ROTATING-STALL CHARACTERISTICS OF A 
ROTOR WITH HIGH HUB-TIP RADIUS RATIO. 
Eleanor L. Costilovv and Merle C. Huppert. August 
1955. 59p. diagrs., photos. (NACA TN 3518) 



A SURVEY OF UNCLASSIFIED AXIAL- FLOW- 
COMPRESSOR LITERATURE. Howard Z. Herzig 
and Arthur G. Hansen. November 1955. i, 88p. 
(NACA RM E55H11) 



CROSS FLOWS IN LAMINAR INCOMPRESSIBLE 
BOUNDARY LAYERS. Arthur G. Hansen and 
Howard Z. Herzig. February 1956. 50p. diagrs., 
photos., tabs. (NACA TN 3651) 

SOME EFFECTS OF GUIDE-VANE TURNING AND 
STATORS ON THE ROTATING STALL CHARACTER- 
ISTICS OF A HIGH HUB-TIP RATIO SINGLE-STAGE 
COMPRESSOR. Eleanor L. Costilow and Merle C. 
Huppert. April 1956. 52p. diagrs., tab. 
(NACA TN 3711) 



STALL PROPAGATION IN AXIAL-FLOW COM- 
PRESSORS. Alan H. Stenning, Anthony R. Kriebel, 
and Stephen R. Montgomery, Massachusetts Institute 
of Technology. June 1956. 83p. diagrs., photos., 
tab. (NACA TN 3580) 



(3.6. 1. 2) 
RADIAL FLOW 



THEORETICAL ANALYSIS OF INCOMPRESSIBLE 
FLOW THROUGH A RADIAL-INLET CENTRIFUGAL 
IMPELLER AT VARIOUS WEIGHT FLOWS. I - 
SOLUTION BY A MATRIX METHOD AND COMPAR- 
ISON WITH AN APPROXIMATE METHOD. Vasily D. 
Prian, James J. Kramer and Chung-Hua Wu. June 
1955. 39p. diagrs., tab. (NACA TN 3448) 

THEORETICAL ANALYSIS OF INCOMPRESSIBLE 
FLOW THROUGH A RADIAL-INLET CENTRIFUGAL 
IMPELLER AT VARIOUS WEIGHT FLOWS. H - 
SOLUTION IN LEADING-EDGE REGION BY RELAX- 
ATION METHODS. James J. Kramer. June 1955. 
19p. diagrs. (NACA TN 3449) 

A SURVEY OF UNCLASSIFIED AXIAL-FLOW- 
COMPRESSOR LITERATURE. Howard Z. Herzig 
and Arthur G. Hansen. November 1955. i, 88p. 
(NACA RM E55H11) 



(3.6. 1. 3) 
MIXED FLOW 



DESIGN AND TEST OF MLXED-FLOW IMPELLERS 
I - AERODYNAMIC DESIGN PROCEDURE. 
Walter M. Osborn and Joseph T. Hamrick. 
September 1952. 42p. diagrs., photo., tab. 
(NACA RM E52E05) 



143 



(3) PROPULSION 



DESIGN AND TEST OF MDCED-FLOW IMPELLERS. 
II - EXPERIMENTAL RESULTS, IMPELLER 
MODEL MFI-1A. Joseph R. Withee, Jr., and 
William L. Beede. September 1952. 28p. diagrs., 
photos., tab. ;NACA RM E52E22) 



A SURVEY OF UNCLASSIFIED AXIAL-FLOW- 
COMPRESSOR LITERATURE. Howard Z. Herzig 
and Arthur G. Hansen. November 1955. i, 88p. 
(NACA RM E55H11) 



(3.6.2) 
STRESS AND VIBRATION 



PRELIMINARY INVESTIGATION OF COMPRESSOR 
BLADE VIBRATION EXCITED BY ROTATING 
STALL. Merle C Huppert, Donald F. Johnson, and 
Eleanor L. Costilow. December 1952. 27p. diagrs., 
photos. (NACA RM E52J15) 



ROTATING-STALL CHARACTERISTICS OF A 
ROTOR WITH HIGH HUB-TIP RADIUS RATIO. 
Eleanor L. Costilow and Merle C. Huppert. August 
1955. 59p. diagrs., photos. (NACA TN 3518) 



EXPERIMENTAL INVESTIGATION OF BLADE 
FLUTTER IN AN ANNULAR CASCADE. J. R. Rowe 
and A. Mendelson. November 1955. 24p. diagrs., 
photos. (NACA TN 3581) 



144 



(3) PROPULSION 



(3.7) 
Turbines 



(3.7.1) 

FLOW THEORY AND 

EXPERIMENT 

VISUALIZATION STUDY OF SECONDARY FLOWS 
IN TURBINE ROTOR TIP REGIONS. Hubert W. 
Allen and Milton G. Kofskey. September 1955. 
33p. diagrs., photos., tab. (NACA TN 3519) 



FLOW OF GAS THROUGH TURBINE LATTICES. 
M. E. Deich. May 1956. 136p. diagrs., photos. 
(NACA TM 1393. Trans, of Russian book: 
Technical Gasdynamics, ch. 7, 1953, p. 312-420) 



(3.7. 1. 1) 
AXIAL FLOW 

ALTITUDE INVESTIGATION OF PERFORMANCE OF 
TURBINE-PROPELLER ENGINE AND ITS COMPO- 
NENTS. Lewis E. Wallner and Martin J. Saari. 
October 5, 1950. 65p. diagrs., photos. (NACA 
RM E50H30) 



TWO-DIMENSIONAL CASCADE INVESTIGATION OF 
THE MAXIMUM EXIT TANGENTIAL VELOCITY 
COMPONENT AND OTHER FLOW CONDITIONS AT 
THE EXIT OF SEVERAL TURBINE BLADE DESIGNS 
AT SUPERCRITICAL PRESSURE RATIOS. Cavour 
H. Hauser and Henry W. Plohr. August 1951. 34p. 
diagrs., photos. (NACA RM E51F12) 



INVESTIGATION OF A RELATED SERIES OF 
TURBINE-BLADE PROFILES IN CASCADE. James 
C. Dunavant and John R. Er*vin. December 1953. 
lOOp, diagrs. (NACA RM L53G15) 

ANALYSIS OF TWO-DIMENSIONAL COMPRESSIBLE- 
FLOW LOSS CHARACTERISTICS DOWNSTREAM OF 
TURBOMACHINE BLADE ROWS IN TERMS OF 
BASIC BOUNDARY-LAYER CHARACTERISTICS. 
Warner L. Stewart. July 1955. 48p. diagrs. (NACA 
TN3515) 

VISUALIZATION STUDY OF SECONDARY FLOWS 
IN TURBINE ROTOR TIP REGIONS. Hubert W. 
Allen and Milton G. Kofskey. September 1955. 
33p. diagrs., photos., tab. (NACA TN 3519) 



(3.7. 1. 3) 
MIXED FLOW 

ANALYTICAL STUDY OF LOSSES AT OFF-DESIGN 
CONDITIONS FOR A FIXED -GEOMETRY TURBINE. 
Warner L. Stewart and David G. Evans. February 
1954. 48p. diagrs., tab. (NACA RM E53K06) 



(3.7.2) 
COOLING 



WIRE CLOTH AS POROUS MATERIAL FOR 
TRANSPIRATION-COOLED WALLS. E. R. G. 
Eckert, Martin R. Kinsler, and Reeves P. Cochran. 
November 1951. 38p. diagrs., photos., tab. (NACA 
RM E51H23) 

ANALYSIS OF COOLANT-FLOW REQUIREMENTS 
FOR AN IMPROVED, INTERNAL-STRUT- 
SUPPORTED, AIR-COOLED TURBINE-ROTOR 
BLADE. Wilson B. Schramm and Alfred J. 
Nachtigall. February 1952. 26p. diagrs., photo. 
(NACA RM E51L13) 

EXPERIMENTAL INVESTIGATION OF AIR-COOLED 
TURBINE BLADES IN TURBOJET ENGINE. XI - 
INTERNAL-STRUT-SUPPORTED ROTOR BLADE. 
Reeves P. Cochran, Francis S. Stepka, and Morton 
H. Krasner. June 1952. 45p. diagrs., photos., 
tabs. (NACA RM E52C21) 



EXPERIMENTAL INVESTIGATION OF AIR-COOLED 
TURBINE BLADES IN TURBOJET ENGINE. XII - 
COOLING EFFECTIVENESS OF A BLADE WITH AN 
INSERT AND WITH FINS MADE OF A CONTINUOUS 
CORRUGATED SHEET. Edward R. Bartoo and John 
L. Clure. August 1952. 33p. diagrs., photos. 
(NACA RM E52F24) 



PROCEDURE FOR CALCULATING TURBINE 
BLADE TEMPERATURES AND COMPARISON OF 
CALCULATED WITH OBSERVED VALUES FOR 
TWO STATIONARY AIR-COOLED BLADES. W. 
Byron Brown, Henry O. Slone, and Hadley T. 
Richards. September 1952. 38p. diagrs. (NACA 
RM E52H07) 



EXPERIMENTAL INVESTIGATION OF AIR-COOLED 
TURBINE BLADES DN TURBOJET ENGINE. 
Xni - ENDURANCE EVALUATION OF SEVERAL 
PROTECTIVE COATINGS APPLIED TO TURBINE 
BLADES OF NONSTRATEGIC STEELS. Edward R. 
Bartoo and John L. Clure. July 1953. 40p. photos., 
diagrs., tabs. (NACA RM E53E18) 

EXPERIMENTAL INVESTIGATION OF AIR-COOLED 
TURBINE BLADES IN TURBOJET ENGINE. XIV - 
ENDURANCE EVALUATION OF SHELL-SUPPORTED 
TURBINE ROTOR BLADES MADE OF TIMKEN 
17-22A(S) STEEL. Francis S. Stepka, H. Robert 
Bear, and John L. Clure. September 1954. 29p. 
diagrs., photos,, tabs. (NACA RM E54F23a) 



EXPERIMENTAL INVESTIGATION OF FREE- 
CONVECTION HEAT TRANSFER IN VERTICAL 
TUBE AT LARGE GRASHOF NUMBERS. E. R. Q. 
EckertandA. J. Diaguila. 1955. ii, 14p. diagrs. : 
photos., tab. (NACA Rept. 1211. Supersedes 
RM E52F30) 



145 



(3) PROPULSION 



CALCULATIONS OF LAMINAR HEAT TRANSFER 
AROUND CYLINDERS OF ARBITRARY CROSS 
SECTION AND TRANSPIRATION-COOLED WALLS 
WITH APPLICATION TO TURBINE BLADE 
COOLING. E. R. G. Eckert and J. N. B. 
Livingood. 1955. ii, 21p. diagrs., tabs. 
(NACA Rept. 1220. Supersedes RM E51F22) 



EXACT SOLUTIONS OF LAMINAR-BOUNDARY- 
LAYER EQUATIONS WITH CONSTANT PROPERTY 
VALUES FOR POROUS WALL WITH VARIABLE 
TEMPERATURE. Patrick L. Donoughe and John 
N. B. Livingood. 1955. ii, 21p. diagrs., tabs. 
(NACA Rept. 1229. Supersedes TN 3151) 



LAMINAR SEPARATION OVER A TRANSPIRATION - 
COOLED SURFACE IN COMPRESSIBLE FLOW. 
Morris Morduchow, Polytechnic Institute of Brook- 
lyn. December 1955. 32p. diagrs. 
(NACA TN 3559) 



FREE-CONVECTION EFFECTS ON HEAT TRANS- 
FER FOR TURBULENT FLOW THROUGH A VERTI- 
CAL TUBE. E. R. G. Eckert, Anthony J. 
Diaguila, and John N. B. Livingood. December 
1955. 24p. diagrs. (NACA TN 3584; 



SUMMARY OF LA MINAR- BOUNDARY- LA* YER 
SOLUTIONS FOR WEDGE -TYPE FLOW~OVER 
CONVECTION- AND TRANSPIRATION-COOLED 
SURFACES. John N. B. Livingood and Patrick L. 
Donoughe. December 1955. 33p. diagrs., tabs 
(NACA TN 3588) 



EXPERIMENTAL INVESTIGATION OF AIR-FLOW 
UNIFORMITY AND PRESSURE LEVEL ON WIRE 
CLOTH FOR TRANSPIRATION-COOLING APPLI- 
CATIONS. Patrick L. Donoughe and Roy A. 
McKinnon. January 1956. 28p. diagrs., photos., 
tab. (NACA TN 3652. Supersedes RM E52E16) 



METHOD OF CALCULATING CORE DIMENSIONS OF 
CROSSFLOW HEAT EXCHANGER WITH PRE- 
SCRIBED GAS FLOWS AND INLET AND EXIT 
STATES. E. R. G. Eckert and Anthony J. Diaguila. 
April 1956. 25p. diagrs. (NACA TN 3655) 



SELECTION OF OPTIMUM CONFIGURATIONS FOR 
HEAT EXCHANGER WITH ONE DOMINATING FILM 
RESISTANCE. E. R. G. Eckert and T. F. Irvine, 
Jr. June 1956. 48p. diagrs. (NACA TN 3713) 



(3.7.3) 
STRESS AND VIBRATION 



PRELIMINARY INVESTIGATION IN J33 TURBOJET 
ENGINE OF SEVERAL ROOT DESIGNS FOR 
CERAMAL TURBINE BLADES. George C. Deutsch, 
Andre J. Meyer, Jr. and William C. Morgan. 
January 1953. 24p. diagrs. , photos. . 2 tabs. 
(NACARM E52K13) 



COMPARATIVE TENSILE STRENGTHS AT 1200° F 
OF VARIOUS ROOT DESIGNS FOR CERMET TUR- 
BINE BLADES. Andre J. Meyer, Jr., Albert 
Kaufman, and Howard F. Calvert. June 1953. 23p. 
diagrs., photos., tabs. (NACA RM E53C25) 



EXPERIMENTAL INVESTIGATION OF AIR-COOLED 
TURBINE BLADES IN TURBOJET ENGINE. XIV - 
ENDURANCE EVALUATION OF SHELL-SUPPORTED 
TURBINE ROTOR BLADES MADE OF TIMKEN 
17-22A(S) STEEL. Francis S. Stepka, H. Robert 
Bear, and John L. Clure. September 1954. 29p. 
diagrs., photos., tabs. (NACA RM E54F23a) 



146 



(3) PROPULSION 



(3.8) 
Friction and Lubrication 



EVALUATION OF A SILICONE-DIESTER LUBRI- 
CANT IN BENCH STUDIES AND IN A TURBOPRO- 
PELLER ENGINE. Robert L Johnson. S, F. 
Murray, and Edmond E. Bisson. Appendix D: 
COPY OF REPORT BY SILICONE PRODUCTS DE- 
PARTMENT OF GENERAL ELECTRIC ON NACA 
SD-17 FLUID. N. G. Hoidstock, General Electric 
Company. May 1954. 32p. diagrs., photos., tabs. 
(NACA RME54B05^ 



(3.8.1) 
THEORY AND EXPERIMENT 



EXPERIMENTAL INVESTIGATION OF ECCENTRI- 
CITY RATIO, FRICTION, AND OIL FLOW OF LONG 
AND SHORT JOURNAL BEARINGS WITH LOAD- 
NUMBER CHARTS. G(eorge) B. DuBois, F(red) W. 
Ocvirk, and R. L. Wehe, Cornell University. 
September 1955. 63p. diagrs., tabs. (NACA TN 
3491) 



FRICTION STUDIES OF GRAPHITE AND MIXTURES 
OF GRAPHITE WITH SEVERAL METALLIC OXIDES 
AND SALTS AT TEMPERATURES TO 1000° F. 
Marshall B. Peterson and Robert L. Johnson. 
February 1956. 16p. diagrs., photos. 
(NACA TN 3657) 



(3. 8.1o 1) 
HYDRODYNAMIC THEORY 



EXPERIMENTS WITH A ROTATING-CYLINDER 
VISCOMETER AT HIGH SHEAR RATES. J. A. Cole, 
R. E. Petersen and H. W. Emmons, Harvard 
University. June 1955. 31p. diagrs., tab. (NACA 
TN 3382) 



(3.8. 1. 2) 
CHEMISTRY OF LUBRICATION 



EVALUATION OF A SILICONE-DIESTER LUBRI- 
CANT IN BENCH STUDIES AND IN A TURBOPRO- 
PELLER ENGINE. Robert L. Johnson. S. F 
Murray and Edmond E. Bisson. Appendix D: 
COPY OF REPORT BY SILICONE PRODUCTS DE- 
PARTMENT OF GENERAL ELECTRIC ON NACA 
SD-17 FLUID. N, G. Hoidstock, General Electric 
Company. May 1954. 32p. diagrs., photos., tabs. 
(NACA RM E54B05) 



SPONTANEOUS IGNITION STUDIES RELATING TO 
LUBRICANTS OF REDUCED FLAMMABILITY. 
Kenneth T. Mecklenborg, Cincinnati University. 
January 1956. 17p. diagrs., tabs. (NACA TN 3560) 



FRICTION STUDIES OF GRAPHITE AND MIXTURES 
OF GRAPHITE WITH SEVERAL METALLIC OXIDES 
AND SALTS AT TEMPERATURES TO 1000° F. 
Marshall B. Peterson and Robert L. Johnson. 
February 1956. 16p. diagrs., photos. 
{NACA TN 3657) 



(3.8. 1. 3) 

SURFACE CONDITIONS 

WEAR OF TYPICAL CARBON-BASE SLIDING SEAL 
MATERIALS AT TEMPERATURES TO 700° F. 
Robert L. Johnson, Max A. Swikert, and John M. 
Bailey. February 1956. 22p. diagrs., photos., tab. 
(NACA TN 3595) 



(3.8.2) 
SLIDING CONTACT SURFACES 



WEAR OF TYPICAL CARBON-BASE SLIDING SEAL 
MATERIALS AT TEMPERATURES TO 700° F. 
Robert L. Johnson, Max A. Swikert, and John M. 
Bailey. February 1956. 22p. diagrs., photos., tab. 
(NACA TN 3595) 



(3.8. 2. 1) 
SLEEVE BEARINGS 

EXPERIMENTAL INVESTIGATION OF ECCENTRI- 
CITY RATIO, FRICTION, AND OIL FLOW OF LONG 
AND SHORT JOURNAL BEARINGS WITH LOAD- 
NUMBER CHARTS. G(eorge) B. DuBois, F(red) W. 
Ocvirk, and R. L. Wehe, Cornell University. 
September 1955. 63p. diagrs., tabs. (NACA TN 
3491) 



(3.8.4) 

SLIDING AND ROLLING 

CONTACT SURFACES 

(3.8.4. 1) 
GEARS 

EVALUATION OF A SILICONE-DIESTER LUBRI- 
CANT IN BENCH STUDIES AND IN A TURBOPRO- 
PELLER ENGINE. Robert L. Johnson. S. F. 
Murray, and Edmond E. Bisson. Appendix D: 
COPY OF REPORT BY SILICONE PRODUCTS DE- 
PARTMENT OF GENERAL ELECTRIC ON NACA 
SD-17 FLUID N. G. Hoidstock. General Electric 
Company. May 1954. 32p. diagrs. photos., tabs. 
(NACA RM E54B05) 



147 



(3) PROPULSION 



(3.8.5) 
LUBRICANTS 



EVALUATION OF A SILICONE-DIESTER LUBRI- 
CANT IN BENCH STUDIES AND IN A TURBOPRO- 
PELLER ENGINE. Robert L. Johnson. S. F 
Murray, and Edmond E. Bisson. Appendix D: 
COPY OF REPORT BY SILICONE PRODUCTS DE- 
PARTMENT OF GENERAL ELECTRIC ON NACA 
SD-17 FLUID N. G Holdstock, General Electric 
Company. May 1954. 32p. diagrs., photos., tabs. 
(NACA RME54B05) 



EXPERIMENTS WITH A ROTA TING-CYLINDER 
VISCOMETER AT HIGH SHEAR RATES. J. A. Cole, 
R. E. Petersen and H. W. Emmons, Harvard 
University. June 1955. 31p. diagrs., tab. (NACA 
TN 3382) 

SPONTANEOUS IGNITION STUDIES RELATING TO 
LUBRICANTS OF REDUCED FLAMMABILITY. 
Kenneth T. Mecklenborg, Cincinnati University. 
January 1956. 17p. diagrs., tabs. (NACA TN 3560) 

FRICTION STUDIES OF GRAPHITE AND MIXTURES 
OF GRAPHITE WITH SEVERAL METALLIC OXIDES 
AND SALTS AT TEMPERATURES TO 1000° F. 
Marshall B. Peterson and Robert L. Johnson. 
February 1956. 16p. diagrs., photos. 
(NACA TN 3657) 



148 



(3) PROPULSION 



(3.9) 
Heat Transfer 



HEAT TRANSFER AT THE FORWARD STAGNATION 
POINT OF BLUNT BODIES. ELi Reshotko and 
Clarence B. Cohen. July 1955. 17p. diagrs. 
(NACA TN 3513) 



VISUAL STUDY OF FREE CONVECTION IN A 
NARROW VERTICAL ENCLOSURE. Ephraim M. 
Sparrow and Samuel J. Kaufman. February 1956. 
14p. diagr., photos. (NACA RM E55L14a) 

METHOD OF CALCULATING CORE DIMENSIONS OF 
CROSSFLOW HEAT EXCHANGER WITH PRE- 
SCRIBED GAS FLOWS AND INLET AND EXIT 
STATES. E. R. G. Eckert and Anthony J. Dlaguila. 
April 1956. 25p. diagrs. (NACA TN 3655) 



SELECTION OF OPTIMUM CONFIGURATIONS FOR 
HEAT EXCHANGER WITH ONE DOMINATING FILM 
RESISTANCE. E. R. G. Eckert and T. F. Irvine, 
Jr. June 1956. 48p. diagrs. (NACA TN 3713) 



(3.9.1) 
THEORY AND EXPERIMENT 



EXPERIMENTAL INVESTIGATION OF AIR-COOLED 
TURBINE BLADES IN TURBOJET ENGINE. XII- 
COOLING EFFECTIVENESS OF A BLADE WITH AN 
INSERT AND WITH FINS MADE OF A CONTINUOUS 
CORRUGATED SHEET. Edward R. Bartoo and John 
L. Clure. August 1952. 33p. diagrs., photos. 
(NACA RM E52F24) 



ANALYSIS OF TURBULENT HEAT TRANSFER, 
MASS TRANSFER, AND FRICTION IN SMOOTH 
TUBES AT HIGH PRANDTL AND SCHMIDT NUM- 
BERS. Robert G. Deissler. 1955. ii, 14p. 
diagrs. (NACA Rept. 1210. Supersedes TN 3145) 



EXPERIMENTAL INVESTIGATION OF FREE- 
CONVECTION HEAT TRANSFER IN VERTICAL 
TUBE AT LARGE GRASHOF NUMBERS. E. R. G. 
Eckert and A. J. Diaguila. 1955. ii, 14p. diagrs., 
photos., tab. (NACA Rept. 1211. Supersedes 
RM E52F30) 



CALCULATIONS OF LAMINAR HEAT TRANSFER 
AROUND CYLINDERS OF ARBITRARY CROSS 
SECTION AND TRANSPIRATION-COOLED WALLS 
WITH APPLICATION TO TURBINE BLADE 
COOLING. E. R. G. Eckert and J. N. B. 
Livingood. 1955. ii, 21p. diagrs., tabs. 
(NACA Rept. 1220. Supersedes RM E51F22) 

THEORETICAL AND EXPERIMENTAL INVESTIGA- 
TION OF HEAT TRANSFER BY LAMINAR NATURAL 
CONVECTION BETWEEN PARALLEL PLATES. 
A. F. Lietzke, 1955. ii, 7p. diagrs. (NACA 
Rept. 1223. Supersedes TN 3328) 



EXACT SOLUTIONS OF LAMINAR-BOUNDARY- 
LAYER EQUATIONS WITH CONSTANT PROPERTY 
VALUES FOR POROUS WALL WITH VARIABLE 
TEMPERATURE. Patrick L. Donoughe and John 
N. B. Livingood. 1955. ii, 21p. diagrs., tabs. 
(NACA Rept. 1229. Supersedes TN 3151) 



PRACTICAL CONSIDERATIONS IN SPECIFIC 
APPLICATIONS OF GAS-FLOW INTERFEROMETRY. 
Walton L. Howes and Donald R. Buchele. July 1955. 
ii, 95p. diagrs., photos. (NACA TN 3507) 



LAMINAR FREE CONVECTION ON A VERTICAL 
PLATE WITH PRESCRIBED NONUNIFORM WALL 
HEAT FLUX OR PRESCRIBED NONUNIFORM WALL 
TEMPERATURE. E. M. Sparrow. July 1955. 34p. 
diagrs. (NACA TN 3508) 



RESPONSE OF HOMOGENEOUS AND TWO- 
MATERIAL LAMINATED CYLINDERS TO SINUSOI- 
DAL ENVIRONMENTAL TEMPERATURE CHANGE, 
WITH APPLICATIONS TO HOT-WIRE ANEMOM- 
ETRY AND THERMOCOUPLE PYROMETRY. 
Herman H. Lowell and Norman (A.) Patton. 
September 1955. ii, 143p. diagrs., tabs. (NACA 
TN 3514) 



HEAT LOSS FROM YAWED HOT WIRES AT SUB- 
SONIC MACH NUMBERS. Virgil A. Sandborn and 
James C. Laurence, September 1955. 44p. 
diagrs., photo. (NACA TN 3563) 



FREE-CONVECTION EFFECTS ON HEAT TRANS- 
FER FOR TURBULENT FLOW THROUGH A VERTI- 
CAL TUBE. E. R. G. Eckert, Anthony J. 
Diaguila. and John N. B. Livingood. December 
1955. 24p. diagrs. (NACA TN 3584; 



SUMMARY OF LAMINAR-BOUNDARY-LAYER 
SOLUTIONS FOR WEDGE-TYPE FLOW OVER 
CONVECTION- AND TRANSPIRATION-COOLED 
SURFACES. John N. B. Livingood and Patrick L. 
Donoughe. December 1955. 33p. diagrs., tabs. 
(NACA TN 3588) 

VISUAL STUDY OF FREE CONVECTION IN A 
NARROW VERTICAL ENCLOSURE. Ephraim M. 
Sparrow and Samuel J. Kaufman. February 1956. 
14p. diagr., photos. (NACA RM E55L14a) 



(3.9. 1. 1) 

CASCADES 



PROCEDURE FOR CALCULATING TURBINE 
BLADE TEMPERATURES AND COMPARISON OF 
CALCULATED WITH OBSERVED VALUES FOR 
TWO STATIONARY AIR-COOLED BLADES. W. 
Byron Brown, Henry O. Slone, and Hadley T. 
Richards. September 1952. 38p. diagrs. (NACA 
RM E52H07) 



149 



(3) PROPULSION 



(3.9.2) 
HEAT EXCHANGERS 



COOLING OF RAM JETS AND TAIL-PIPE 
BURNERS - ANALYTICAL METHOD FOR DETER- 
MINING TEMPERATURES OF COMBUSTION CHAM- 
BER HAVING ANNULAR COOLING PASSAGE. 
William K. Koffel, Eugene Stamper, and Newell D. 
Sanders. March 21, 1950. 51p. diagrs,, tab. 
(NACA RM E9L09) 



METHOD OF CALCULATING CORE DIMENSIONS OF 
CROSS FLOW HEAT EXCHANGER WITH PRE- 
SCRIBED GAS FLOWS AND INLET AND EXIT 
STATES. E. R. G. Eckert and Anthony J. Diagulla. 
April 1956. 25p. diagrs. (NACA TN 3655) 



SELECTION OF OPTIMUM CONFIGURATIONS FOR 
HEAT EXCHANGER WITH ONE DOMINATING FILM 
RESISTANCE. E. R. G. Eckert and T. F. Irvine, 
Jr. June 1956. 48p. diagrs. (NACA TN 3713) 



(3.9.2.4) 
REGENERATORS 



INVESTIGATION OF INTERNAL REGENERATIVE 
FUEL-HEATING SYSTEM FOR 20-INCH RAM JET. 
Sol Baker and Eugene Perchonok. September 1, 
1949. 22p. diagrs., photos. (NACA RM E9F20) 



150 



{3) PROPULSION 



(3.10) 
Cooling of Engines 



WIRE CLOTH AS POROUS MATERIAL FOR 
TRANSPIRATION-COOLED WALLS. E. R. G. 
Eckert, Martin R. Kinsler, and Reeves P. Cochran. 
November 1951. 38p. diagrs., photos., tab. (NACA 
RM E51H23) 



CHARTS OF BOUNDARY-LAYER MASS FLOW AND 
MOMENTUM FOR INLET PERFORMANCE ANALY- 
SIS MACH NUMBER RANGE, 0.2 TO 5.0. Paul C. 
Simon and Kenneth L. Kowalskl. November 1955. 
32p. diagrs., tab. (NACA TN 3583) 



EXPERIMENTAL INVESTIGATION OF AIR- FLOW 
UNIFORMITY AND PRESSURE LEVEL ON WIRE 
CLOTH FOR TRANSPIRATION-COOLING APPLI- 
CATIONS. Patrick L. Donoughe and Roy A. 
McKinnon. January 1956. 28p. diagrs., photos., 
tab. (NACA TN 3652. Supersedes RM E52E16) 



(3.10.2) 
GAS-TURBINE SYSTEMS 



COOLING OF RAM JETS AND TAIL-PIPE 
BURNERS - ANALYTICAL METHOD FOR DETER- 
MINING TEMPERATURES OF COMBUSTION CHAM- 
BER HAVING ANNULAR COOLING PASSAGE. 
William K. Koffel, Eugene Stamper, and Newell D. 
Sanders. March 21, 1950. 51p. diagrs., tab. 
(NACA RM E9L09) 



EXPERIMENTAL INVESTIGATION OF THRUST 
AUGMENTATION OF 4000-POUND-THRUST AXIAL- 
FLOW -TYPE TURBOJET ENGINE BY INTERSTAGE 
INJECTION OF WATER- ALCOHOL MIXTURES IN 
COMPRESSOR. John H. Povolny, James W. Useller, 
and Louis J. Chelko. April 6, 1950. 42p. diagrs., 
photos., tab. (NACA RM E9K30) 



WIRE CLOTH AS POROUS MATERIAL FOR 
TRANSPIRATION-COOLED WALLS. E. R. G. 
Eckert, Martin R. Kinsler, and Reeves P, Cochran. 
November 1951. 38p. diagrs., photos., tab. (NACA 
RM E51H23) 



ANALYSIS OF COOLANT-FLOW REQUIREMENTS 
FOR AN IMPROVED, INTERNAL-STRUT- 
SUPPORTED, AIR-COOLED TURBINE-ROTOR 
BLADE. Wilson B. Schramm and Alfred J. 
Nachtigall. February 1952. 26p. diagrs., photo. 
(NACARM E51L13) 



EXPERIMENTAL INVESTIGATION OF AIR-COOLED 
TURBINE BLADES IN TURBOJET ENGINE. XI - 
INTERNAL-STRUT-SUPPORTED ROTOR BLADE. 
Reeves P. Cochran, Francis S. Stepka, and Morton 
H. Krasner. June 1952. 45p. diagrs., photos., 
tabs. (NACA RM E52C21) 



PRELIMINARY AIR-FLOW AND THRUST CALIBRA- 
TIONS OF SEVERAL CONICAL COOLING-AIR 
EJECTORS WITH A PRIMARY TO SECONDARY 
TEMPERATURE RATIO OF 1.0. I - DIAMETER 
RATIOS OF 1.21 AND 1.10. W. K. Greathouse and 
D. P. Hollister. July 1952. 24p. diagrs. 
(NACA RM E52E21) 

EXPERIMENTAL INVESTIGATION OF AIR-COOLED 
TURBINE BLADES IN TURBOJET ENGINE. XII- 
COOLING EFFECTIVENESS OF A BLADE WITH AN 
INSERT AND WITH FINS MADE OF A CONTINUOUS 
CORRUGATED SHEET. Edward R. Bartoo and John 
L. Clure. August 1952. 33p. diagrs., photos. 
(NACA RM E52F24) 



PRELIMINARY AIR-FLOW AND THRUST CAL3RA- 
TIONS OF SEVERAL CONICAL COOLING -AIR 
EJECTORS WITH A PRIMARY TO SECONDARY 
TEMPERATURE RATIO OF 1.0. U - DIAMETER 
RATIOS OF 1.06 AND 1.40. W. K. Greathouse and 
D. P. Hollister. August 1952. 35p. diagrs. 
(NACA RM E52F26) 



EXPERIMENTAL INVESTIGATION OF AIR-COOLED 
TURBINE BLADES IN TURBOJET ENGINE. 
XHI - ENDURANCE EVALUATION OF SEVERAL 
PROTECTIVE COATINGS APPLIED TO TURBINE 
BLADES OF NONSTRATEGIC STEELS. Edward R. 
Bartoo and John L. Clure. July 1953. 4 Op. photos., 
diagrs., tabs. (NACA RM E53E18) 

EXPERIMENTAL INVESTIGATION OF FREE- 
CONVECTION HEAT TRANSFER IN VERTICAL 
TUBE AT LARGE GRASHOF NUMBERS. E. R. G. 
Eckert and A. J. Diaguila. 1955. 11, 14p. diagrs., 
photos., tab. (NACA Rept. 1211. Supersedes 
RM E52F30) 



CALCULATIONS OF LAMINAR HEAT TRANSFER 
AROUND CYLINDERS OF ARBITRARY CROSS 
SECTION AND TRANSPIRATION-COOLED WALLS 
WITH APPLICATION TO TURBINE BLADE 
COOLING. E. R. G. Eckert and J. N. B. 
Livingood. 1955. ii, 21p. diagrs., tabs. 
(NACA Rept. 1220. Supersedes RM E51F22) 



LAMINAR FREE CONVECTION ON A VERTICAL 
PLATE WITH PRESCRIBED NONUNIFORM WALL 
HEAT FLUX OR PRESCRIBED NONUNIFORM WALL 
TEMPERATURE. E. M. Sparrow. July 1955. 34p. 
diagrs. (NACA TN 3508) 



FREE -CONVECTION EFFECTS ON HEAT TRANS- 
FER FOR TURBULENT FLOW THROUGH A VERTI- 
CAL TUBE. E. R. G. Eckert, Anthony J. 
Diaguila, and John N. B. Livingood. December 
1955. 24p. diagrs. (NACA TN 3584; 



EXPERIMENTAL INVESTIGATION OF AIR-FLOW 
UNIFORMITY AND PRESSURE LEVEL ON WIRE 
CLOTH FOR TRANSPIRATION -COOLING APPLI- 
CATIONS. Patrick L. Donoughe and Roy A. 
McKinnon. January 1956. 28p. diagrs., photos., 
tab. (NACA TN 3652. Supersedes RM E52E16) 



151 



(3) PROPULSION 



METHOD OF CALCULATING CORE DIMENSIONS OF 
CROSSFLOW HEAT EXCHANGER WITH PRE- 
SCRIBED GAS FLOWS AND INLET AND EXIT 
STATES. E. R. G. Eckert and Anthony J. Diaguila. 
April 1956. 25p. diagrs. (NACA TN 3655) 



PERFORATED SHEETS AS A POROUS MATERIAL 
FOR DISTRIBUTED SUCTION AND INJECTION. 
Robert E. Dannenberg, Bruno J. Gaxnbucci, and 
James A. Weiberg. April 1956. 27p. diagrs., 
photos. (NACA TN 3669) 



SELECTION OF OPTIMUM CONFIGURATIONS FOR 
HEAT EXCHANGER WITH ONE DOMINATING FILM 
RESISTANCE. E. R. G. Eckert and T. F. Irvine, 
Jr. June 1956. 48p. diagrs. (NACA TN 3713) 



(3.10.3) 
RAMJETS 



INVESTIGATION OF EFFECTS OF MOVABLE 
EXHAUST-NOZZLE PLUG ON OPERATIONAL PER- 
FORMANCE OF 20-INCP RAM JET. William H. 
Sterbentz and Fred A. Wilcox. July 27, 1948. 32p. 
diagrs., photos. (NACA RM E8D22) 



COOLING OF RAM JETS AND TAIL-PIPE 
BURNERS - ANALYTICAL METHOD FOR DETER- 
MINING TEMPERATURES OF COMBUSTION CHAM- 
BER HAVING ANNULAR COOLING PASSAGE. 
William K. Koffel, Eugene Stamper, and Newell D. 
Sanders. March 21, 1950. 5lp. diagrs., tab. 
(NACA RM E9L09) 



WIRE CLOTH AS POROUS MATERIAL FOR 
TRANSPIRATION -COOLED WALLS. E. R. G. 
Eckert, Martin R. Kinsler, and Reeves P. Cochran. 
November 1951. 38p. diagrs., photos., tab. (NACA 
RM E51H23) 



LAMINAR FREE CONVECTION ON A VERTICAL 
PLATE WITH PRESCRIBED NONUNIFORM WALL 
HEAT FLUX OR PRESCRIBED NONUNIFORM WALL 
TEMPERATURE. E. M. Sparrow. July 1955. 34p. 
diagrs. (NACA TN 3508) 



EXPERIMENTAL INVESTIGATION OF AIR-FLOW 
UNIFORMITY AND PRESSURE LEVEL ON WIRE 
CLOTH FOR TRANSPIRATION-COOLING APPLI- 
CATIONS. Patrick L. Donoughe and Roy A. 
McKinnon. January 1956. 28p. diagrs., photos., 
tab. (NACA TN 3652. Supersedes RM E52E16) 



152 



(3) PROPULSION 



(3.11) 
Properties of Gases 



THEORETICAL PERFORMANCE OF SOME ROCKET 
PROPELLANTS CONTAINING HYDROGEN, 
NITROGEN, AND OXYGEN. Riley O. Miller and 
Paul M. Ordin. May 26, 1948. 53p. diagrs., tabs. 

(NACA RM E8A30) 



THERMODYNAMIC PROPERTIES OF GASEOUS 
NITROGEN. Harold W. Woolley, National Bureau 
of Standards. March 1956. 114p. diagrs., tabs. 
(NACA TN 3271) 



GENERALIZED TABLES OF CORRECTIONS TO 
THERMODYNAMIC PROPERTIES FOR NON POLAR 
GASES. Harold W. Woolley and William S. Benedict, 
National Bureau of Standards. March 1956. 62p. 
diagrs., tabs. (NACA TN 3272) 



HEAT CAPACITY LAG OF GASEOUS MIXTURES. 
Thomas D. Rossing, Robert C. Amme, and Sam 
Legvold, Iowa State College. March 1956 35p. 
diagrs., tabs. (NACA TN 3558) 



(3.11.1) 
KINETIC 



THEORETICAL PERFORMANCE OF JP-4 FUEL 
AND LIQUID OXYGEN AS A ROCKET PROPEL- 
LANT. I - FROZEN COMPOSITION. Vearl N. Huff 
and Anthony Fortini. April 1956. 35p. diagrs., 
tabs. (NACA RM E56A27) 



(3.11.2) 
THERMODYNAMIC 



PRELIMINARY EVALUATION OF THE AIR AND 
FUEL SPECIFIC-IMPULSE CHARACTERISTICS OF 
SEVERAL POTENTIAL RAM-JET FUELS. II - 
MAGNESIUM AND MAGNESIUM - OCTENE-1 
SLURRIES. Benson E. Gammon. May 2, 1951. 
15p. diagrs. (NACA RM E51C23) 



PRELIMINARY EVALUATION OF THE AIR AND 
FUEL SPECIFIC -IMPULSE CHARACTERISTICS OF 
SEVERAL POTENTIAL RAM-JET FUELS. IV - 
HYDROGEN, a-METHYLNAPHTHALENE, AND 
CARBON. Benson E. Gammon. August 1951. 22p. 
diagrs. (NACA RM E51F05) 



153 



(3) PROPULSION 



(3.12) 

Accessories and Accessory 

Functions 



(3.12.1) 
FUEL SYSTEMS 



AN EXPERIMENTAL COMPARISON OF THE 
LAGRANGIAN AND EULERIAN CORRELATION 
COEFFICIENTS IN HOMOGENEOUS ISOTROPIC 
TURBULENCE. William R. Mickelsen. October 
1955. 42p. diagrs. (NACA TN 3570) 



(3. 12. 1.4) 
TURBOJET ENGINES 



ANALOG STUDY OF INTERACTING AND NON- 
INTERACTING MULTIPLE -LOOP CONTROL SYS- 
TEMS FOR TURBULENT ENGINES. George J. 
Pack and W. E. Phillips, Jr. 1955. ii, 13p. 
diagrs. (NACA Rept. 1212. Supersedes TN 3112) 



(3. 12. 1. 6) 

PULSE-JET ENGINES 



INVESTIGATION OF INTERNAL REGENERATIVE 
FUEL-HEATING SYSTEM FOR 20-INCH RAM JET. 
Sol Baker and Eugene Perchonok. September 1, 
1949. 22p. diagrs., photos. (NACA RM E9F20) 



FREE-FLIGHT PERFORMANCE OF 16-INCH- 
DIAMETER SUPERSONIC RAM-JET UNITS. I - 
FOUR UNITS DESIGNED FOR COMBUSTION - 
CHAMBER-INLET MACH NUMBER OF 0.12 AT 
FREE-STREAM MACH NUMBER OF 1.6 (UNITS A- 
A-3, A-4. AND A-5). William W. Carlton and 
Wesley E. Messing. September 22, 1049. 51p. 
diagrs., photos. (NACA RM E9F22) 



(3. 12. 1.7) 
RAM -JET ENGINES 



INVESTIGATION OF INTERNAL REGENERATIVE 
FUEL-HEATING SYSTEM FOR 20-INCH RAM JET. 
Sol Baker and Eugene Perchonok. September 1, 
1949. 22p. diagrs., photos. (NACA RM E9F20) 



FREE-FLIGHT PERFORMANCE OF 16-INCH- 
DIAMETER SUPERSONIC RAM -JET UNITS. I - 
FOUR UNITS DESIGNED FOR COMBUSTION- 
CHAMBER-INLET MACH NUMBER OF 0.12 AT 
FREE-STREAM MACH NUMBER OF 1.6 (UNITS A-2, 
A-3, A-4, AND A-5). William W. Carlton and 
Wesley E. Messing. September 22, 1949. 51p. 
diagrs., photos. (NACA RM E9F22) 



(3. 12. 1. 8) 
ROCKET ENGINES 



IGNITION -DELAY CHARACTERISTICS IN MODIFIED 
OPEN-CUP APPARATUS OF SEVERAL FUELS 
WITH NITRIC ACID OXIDANTS WITHIN TEMPERA- 
TURE RANGE 70° TO -105° F. Riley O. Miller. 
December 1951. 30p. diagrs., 4 tabs. 
(NACA RME51J11) 



(3.12.2) 
IGNITION SYSTEMS 



EFFECT OF SPARK REPETITION RATE ON THE 
IGNITION LIMITS OF A SINGLE TUBULAR COM- 
BUSTOR. Hampton H. Foster. December 1951. 
12p. diagrs., tab. (NACA RM E51J18) 



SPARK IGNITION OF FLOWING GASES. V - AP- 
PLICATION OF FUEL-AIR-RATIO AND INITIAL- 
TEMPERATURE DATA TO IGNITION THEORY. 
Clyde C. Swett, Jr. November 1955. 19p. diagrs. 
(NACA RM E55I16) 



(3.12.3) 
STARTING SYSTEMS 



FREE-JET TESTS OF A 6.5-INCH-DIAMETER 
RAM-JET ENGINE AT MACH NUMBERS OF 1.81 
AND 2.00. Maxime A. Faget, Raymond S, Watson, 
and Walter A. Bartlett, Jr. March 7, 1951. 38p. 
diagrs., photos. (NACA RM L50L06) 



154 



(3) PROPULSION 



(3.13) 
Vibration and Flutter 



ROTATJNG-STALL CHARACTERISTICS OF A 
ROTOR WITH HIGH HUB-TIP RADIUS RATIO. 
Eleanor L. Costilow and Merle C. Huppert. August 
1955. 59p. diagrs., photos. (NACA TN 3518) 



STALL PROPAGATION IN AXIAL -FLOW COM- 
PRESSORS. Alan H. Stenning, Anthony R. Kriebel, 
and Stephen R. Montgomery, Massachusetts Institute 
of Technology. June 1956. 83p. diagrs., photos., 

tab. (NACA TN 3580) 



FLUTTER OF THIN PROPELLER BLADES, 
INCLUDING EFFECTS OF MACH NUMBER, 
STRUCTURAL DAMPING, AND VIBRATORY-STRESS 
MEASUREMENTS NEAR THE FLUTTER 
BOUNDARIES. Harvey H. Hubbard, Marvin F. 
Burgess, and Maurice A. Sylvester. June 1956. 
25p. diagrs., tab. (NACA TN 3707) 



(4) 



(4) 

AIRCRAFT LOADS 

AND CONSTRUCTION 



155 



(4) AIRCRAFT LOADS AND CONSTRUCTION 



(4.1) 
Loads 



(4.1.1) 
AERODYNAMIC 



AERODYNAMIC MEASUREMENTS MADE DURING 
NAVY INVESTIGATION OF HUMAN TOLERANCE 
TO WIND BLASTS. Donald L. Loving. March 11, 
1947. 34p. diagrs., photos., 2 tabs. (NACA 
RM L7C25) 



AERODYNAMIC INVESTIGATION OF A PARABOLIC 
BODY OF REVOLUTION AT MACH NUMBER OF 
1.92 AND SOME EFFECTS OF AN ANNULAR JET 
EXHAUSTING FROM THE BASE. Eugene S. Love. 
February 8, 1950. 75p. diagrs., photos., tab. 
(NACA RM L9K09) 



NOTES ON LOW-LIFT BUFFETING AND WING 
DROPPING AT MACH NUMBERS NEAR 1. Paul E. 
Purser. March 1G, 19j1. 22p. diagrs., tab. 
(NACA RM L51A30) 



LOW-LIFT BUFFET CHARACTERISTICS OB- 
TAINED FROM FLIGHT TESTS OF UNSWEPT THIN 
INTERSECTING SURFACES AND OF THICK 35° 
SWEPTBACK SURFACES. Homer P. Mason. 
January 1953. 21p. diagrs., photos. (NACA 
RM L52H12) 



THE LATERAL CONTROL CHARACTERISTICS OF 
CONSTANT-PERCENT-CHORD TRAILING-EDGE 
ELEVONS ON A POINTED WING OF ASPECT RATIO 
2 AT MACH NUMBERS UP TO 0.95. Verlin D. Reed 
and Donald W. Smith. August 1953. 105p. diagrs., 
photo., tabs. (NACA RM A53F03) 



CALIBRATION OF STRAIN-GAGE INSTALLATIONS 
IN AIRCRAFT STRUCTURES FOR THE MEASURE- 
MENT OF FLIGHT LOADS. T. H. Skopinski, 
William S. Aiken, Jr. and Wilber B. Huston. 1954. 
ii, 29p. diagrs., 10 tabs. (NACA Rept. 1178. 
Formerly TN 2993; RM L52G31) 



MEASUREMENTS OF NORMAL-FORCE- 
COEFFICIENT FLUCTUATION ON FOUR 9- 
PERCENT-THICK AIRFOILS HAVING DIFFERENT 
LOCATIONS OF MAXIMUM THICKNESS. Milton D. 
Humphreys. April 1954. 21p. diagrs., photos. 
(NACA RM L54222) 



(4. 1. l. 1) 
WINGS 



MEASUREMENTS OF THE CHORDWISE PRESSURE 
DISTRIBUTIONS OVER THE WING OF THE XS-1 
RESEARCH AIRPLANE IN FLIGHT. De E. Beeler, 
Milton D. McLaughlin, and Dorothy C. Clift. 
August 4, 1948. 35p. diagrs., photo., tab. (NACA 
RM L8G21) 



TABULATED PRESSURE COEFFICIENTS AND 
AERODYNAMIC CHARACTERISTICS MEASURED ON 
THE WING OF THE BELL X-l AIRPLANE IN PULL- 
UPS AT MACH NUMBERS FROM 0.53 TO 0.99. 
Ronald J. Knapp and Gertrude V. Wilken. 
November 1, 1950. 77p. diagrs., photo., 11 tabs. 
(NACA RM L50H28) 



REVIEW OF SOME RECENT DATA ON BUFFET 
BOUNDARIES. Paul E. Purser and John A. Wyss. 
May 23, 1951. lip. diagrs. (NACA RM L51 E02a) 



TABULATED PRESSURE COEFFICIENTS AND 
AERODYNAMIC CHARACTERISTICS MEASURED 
ON THE WING OF THE BELL X-l AIRPLANE IN 
AN UNACCELERATED STALL AND IN PULL-UPS 
AT MACH NUMBERS OF 0.74, 0.75, 0.94, AND 
0.97. Lawrence A. Smith. June 19, 1951. 49p. 
diagrs., photo., tabs. (NACA RM L51B23) 



TRANSONIC -WING INVESTIGATION IN THE 
LANGLEY 8-FOOT HIGH-SPEED TUNNEL AT HIGH 
SUBSONIC MACH NUMBERS AND AT A MACH NUM- 
BER OF 1.2. ANALYSIS OF PRESSURE DISTRIBU- 
TION OF WING-FUSELAGE CONFIGURATION HAV- 
ING A WING OF 45° SWEEPBACK, ASPECT RATIO 
4, TAPER RATIO 0.6, AND NACA 65A006 AIRFOIL 
SECTION. Donald L. Loving and Bruce B. 
Estabrooks. September 1951. 132p. diagrs., photos. 
(NACARM L51F07) 



A CORRELATION WITH FLIGHT TESTS OF RE- 
SULTS OBTAINED FROM THE MEASUREMENT OF 
WING PRESSURE DISTRIBUTIONS ON A 1/4-SCALE 
MODEL OF THE X-l AIRPLANE (10-PERCENT- 
THICK WING). Jack F. Runckel and James H. 
Henderson. September 1952. 60p. diagrs., photos., 
tab. (NACA RM L52E29) 



LONGITUDINAL FLIGHT CHARACTERISTICS OF 
THE BELL X-5 RESEARCH AIRPLANE AT 59° 
SWEEPBACK WITH MODIFIED WING ROOTS. 
James A. Martin. August 1953. 25p. diagrs., 
photos., tab. (NACA RM L53E28) 



156 



(4) AIRCRAFT LOADS AND CONSTRUCTION 



ON THE USE OF THE INDICIAL FUNCTION CON- 
CEPT IN THE ANALYSIS OF UNSTEADY MOTIONS 
OF WINGS AND WING-TAIL COMBINATIONS. 

Murray Tobak. 1954. hi, 43p. diagrs. (NACA 
Rept. 1188) 



A COMPARISON OF THE SPANWISE LOADING 
CALCULATED BY VARIOUS METHODS WITH EX- 
PERIMENTAL LOADINGS OBTAINED ON A 45° 
SWEPTBACK WING OF ASPECT RATIO 8.C2 AT A 
REYNOLDS NUMBER OF 4.0 x 10 6 . William C. 
Schneider. 1954. ii, Up. diagrs., tab. 
(NACA Rept. 1208. Supersedes RM L51G30) 



DISTRIBUTION OF LIFT AND PITCHING MOMENT 
BLTVV£EN WING AND FUSELAGE AND EFFECTS 
OF WING FLEXIBILITY AND DIVE BRAKE ON A 
1 30-SCALE SEMISPAN MODEL OF THE BELL X-5 
AIRPLANE AT TRANSONIC SPEEDS AS DETER- 
MINED GY THE NACA WING- FLOW METHOD. 
Garland J. Morris and Norman S. Silsby. March 
1C54. 4Gp. diagrs., photos., tab. 
(NACA RM L54A11) 



A METHOD FOR THE DESIGN OF SWEPTBACK 
WINGS WARPED TO PRODUCE SPECIFIED FLIGHT 
CHARACTERISTICS AT SUPERSONIC SPEEDS. 
Warren A. Tucker. 1955. i. 17p. diagrs., tabs. 
(NACA Rept. 1226. Supersedes RM L51F08) 



CALCULATED SPANWISE LIFT DISTRIBUTIONS, 
INFLUENCE FUNCTIONS, AND INFLUENCE COEF- 
FICIENTS FOR UNSWEPT WINGS IN SUBSONIC 
FLOW. Franklin W. Diederich and Martin Zlotnick. 
1955. ii, 69p. diagrs., tabs. (NACA Rept. 1228. 
Supersedes TN 3014) 



CALCULATED SPANWISE LIFT DISTRIBUTIONS 
AND AERODYNAMIC INFLUENCE COEFFICIENTS 
FOR SWEPT WINGS IN SUBSONIC FLOW. 
Franklin W. Diederich and Martin Zlotnick. 
October 1955. 173p. diagrs., tabs. (NACA 
TN 3476) 



FLOW STUDIES ON DROOPED-LEADING-EDGE 
DELTA WINGS AT SUPERSONIC SPEED. William 
H. Michael, Jr. January 1956. 29p. diagrs., 
photos. (NACA TN 3614) 



PRELIMINARY FLIGHT SURVEY OF AERODY- 
NAMIC NOISE ON AN AIRPLANE WING. Harold R, 
Mull and Joseph S. Algranti. March 1956. 8p. 
diagrs. (NACA RM E55K07) 



A THEORETICAL STUDY OF THE AERODYNAMICS 
OF SLENDER CRUCIFORM-WING ARRANGEMENTS 
AND THEIR WAKES. John R. Spreiter and Alvin H. 
Sacks. March 1956. i, 67p. diagrs., photos., tabs. 
(NACA TN 3528) 



(4. 1.1.1. 1) 
Steady Loads 



AERODYNAMIC CHARACTERISTICS INCLUDING 
PRESSURE DISTRIBUTIONS OF A FUSELAGE AND 
THREE COMBINATIONS OF THE FUSELAGE WITH 
SWEPT -BACK WINGS AT HIGH SUBSONIC SPEEDS. 
Fred B. Sutton and Andrew Martin. February 6, 
1951. 117p, diagrs., photos., tabs. 
(NACA RM A50J26a) 



A COMPARISON OF THE EXPERIMENTAL AND 
THEORETICAL LOADING OVER TRIANGULAR 
WINGS IN SIDESLIP AT SUPERSONIC SPEEDS. 
John W. Boyd. May 18, 1951. 58p. diagrs., photo., 
tabs. (NACA RM A51C13) 



THE EFFECTS OF REYNOLDS NUMBER AT MACH 
NUMBERS UP TO 0.94 ON THE LOADING ON A 35° 
SWEPTBACK WING HAVING NACA 65^012 
STREAMWISE SECTIONS. Bruce E. Tinling and 
Armando E. Lopez. June 1952. 115p. diagrs., 
photos., tabs. (NACA RM A52B20) 



CHORDWISE PRESSURE DISTRIBUTION AT HIGH 
SUBSONIC SPEEDS NEAR MIDSEMISPAN OF A 
TAPERED 35° SWEPTBACK WING OF ASPECT 
RATIO 4 HAVING NACA 65A006 AIRFOIL SECTIONS 
AND EQUIPPED WITH VARIOUS SPOILER AILER- 
ONS. Alexander D. Hammond and Barbara M. 
McMullan. June 1952. 76p. diagrs., tabs. 
(NACA RM L52C28) 



INVESTIGATION OF THE EFFECT OF CHORDWISE 
POSITIONING AND SHAPE OF AN UNDERWING NA- 
CELLE ON THE HIGH-SPEED AERODYNAMIC 
CHARACTERISTICS OF A 45° SWEPTBACK 
TAPERED-IN-THICKNESS-RATIO WING OF AS- 
PECT RATIO 6. H. Norman Silvers and Thomas J. 
King, Jr. January 1953. 50p. diagrs. 
(NACA RM L52K25) 



PRESSURE DISTRIBUTION AT MACH NUMBERS UP 
TO 0.90 ON A CAMBERED AND TWISTED WING 
HAVING 40° OF SWEEPBACK AND AN ASPECT 
RATIO OF 10, INCLUDING THE EFFECTS OF 
FENCES. Frederick W. Boltz and Harry H. 
Shibata. March 1953. 133p. diagrs., photos., tabs. 
(NACA RM A52K20) 



THE EFFECT AT HIGH SUBSONIC SPEEDS OF A 
FLAP-TYPE AILERON ON THE CHORDWISE PRES- 
SURE DISTRIBUTION NEAR MIDSEMISPAN OF A 
TAPERED 35° SWEPTBACK WING OF ASPECT 
RATIO 4 HAVING NACA 65A006 AIRFOIL SECTION. 
Alexander D. Hammond and Barbara M. Kefler. 
May 1953. 89p. diagrs., tab. {NACA RM L53C23) 



157 



(4) AIRCRAFT LOADS AND CONSTRUCTION 



CHORDWISE PRESSURES AND SECTION FORCE 
AND MOMENT COEFFICIENTS AT HIGH SUBSONIC 
SPEEDS NEAR MIDSPAN OF A TAPERED 35° 
SWEPTBACK WING WITH A FLAP-TYPE CONTROL 
AND AN ATTACHED TAB. Alexander D. Hammond 
and Barbara M. Keffer. March 1954. 57p. diagrs., 
35 tabs. (NACA RM L54A22) 



EFFECTS OF OPERATING PROPELLERS ON THE 
WING-SURFACE PRESSURES OF A FOUR-ENGINE 
TRACTOR AIRPLANE CONFIGURATION HAVING A 
WING WITH 40° OF SWEEPBACK. Carl D. Kolbe 
and Frederick W. Boltz, April 1954. 133p. 
diagrs., photo., 19 tabs. (NACA RM A53L29) 



THE EFFECT OF BLUNT-TRAILTNG-EDGE MODI- 
FICATIONS ON THE HIGH-SPEED STABILITY AND 
CONTROL CHARACTERISTICS OF A SWEPT-WING 
FIGHTER AIRPLANE. Melvin Sadoff, Frederick H. 
Matte son, and Rudolph D. Van Dyke, Jr. May 1954. 
55p. diagrs., photos., tab. (NACA RM A54C31) 



WING-LOAD MEASUREMENTS OF THE BELL X-5 
RESEARCH AIRPLANE AT A SWEEP ANGLE OF 
58.7°. Richard D. Banner, Robert D. Reed, and 
William L. Marcy. April 1955. 22p. diagrs., 
photo., tab. (NACA RM H55A11) 



AERODYNAMICS OF A RECTANGULAR WING OF 
INFINITE ASPECT RATIO AT HIGH ANGLES OF 
ATTACK AND SUPERSONIC SPEEDS. John C. 
Martin and Frank S. Malvestuto, Jr. July 1955. 
114p. diagrs., tab. (NACA TN 3421) 



FLOW STUDIES ON FLAT-PLATE DELTA WINGS 
AT SUPERSONIC SPEED. William H. Michael, Jr. 
July 1955. 40p. diagrs., photos. (NACA TN 3472) 



CORRECTION OF ADDITIONAL SPAN LOADINGS 
COMPUTED BY THE WEISSINGER SEVEN-POINT 
METHOD FOR MODERATELY TAPERED WINGS 
OF HIGH ASPECT RATIO. John DeYoung and 
Walter H. Barling, Jr. July 1955. 31p. diagrs. 
(NACA TN 3500) 



THEORETICAL SPAN LOAD DISTRIBUTIONS AND 
ROLLING MOMENTS FOR SIDESLIPPING WINGS 
OF ARBITRARY PLAN FORM IN INCOMPRESSIBLE 
FLOW. M. J. Queijo. December 1955. 45p. 
diagrs. (NACA TN 3605) 



(4. 1. 1.1.2) 

Maneuvering 



EFFECT OF FORMATION POSITION ON LOAD 
FACTORS OBTAINED ON F2H AIRPLANES. Carl R. 
Huss and Harold A. Hamer. December 1951. 15p. 
diagrs., 3 tabs. (NACA RM L51I05) 



TIME HISTORIES OF MANEUVERS PERFORMED 
WITH AN F-86A AIRPLANE DURING SQUADRON 
OPERATIONS. Harold A. Hamer and Campbell 
Henderson. February 1952 90p. diacrrs.. 3 tabs. 
(NACA RM L51K30) 



AILERON AND ELEVATOR HINGE MOMENTS OF 
THE BELL X-l AIRPLANE MEASURED IN TRAN- 
SONIC FLIGHT. Hubert M. Drake and John B. 
McKay. June 1953. 27p. diagrs. 
(NACA RM L53E04) 



WIND-TUNNEL INVESTIGATION OF THE EFFECTS 
OF STEADY ROLLING ON THE AERODYNAMIC 
LOADING CHARACTERISTICS OF A 45° SWEPT- 
BACK WING AT HIGH SUBSONIC SPEEDS. James 
W. Wiggins and Richard E. Kuhn. November 1953. 
22p. diagrs., photos. (NACA RM L53J01a) 



ON THE USE OF THE INDICIAL FUNCTION CON- 
CEPT IN THE ANALYSIS OF UNSTEADY MOTIONS 
OF WINGS AND WING-TAIL COMBINATIONS. 
Murray Tobak. 1954. iii, 43p. diagrs. (NACA 
Rept. 1188) 



GENERALIZED INDICIAL FORCES ON DEFORMING 
RECTANGULAR WINGS IN SUPERSONIC FLIGHT. 
Harvard Lomax, Franklyn B. Fuller and Loma 
Sluder. 1955. ii, 27p. diagrs., tab. 
(NACA Rept. 1230. Supersedes TN 3286) 



A FLIGHT EVALUATION OF THE LONGITUDINAL 
STABILITY CHARACTERISTICS ASSOCIATED WITH 
THE PITCH-UP OF A SWEPT-WING AIRPLANE IN 
MANEUVERING FLIGHT AT TRANSONIC SPEEDS. 
Seth B. Anderson and Richard S. Bray. 1955. ii, 
12p. diagrs., photo., tab. (NACA Rept. 1237. 
Supersedes RM A51I12) 



WING-LOAD MEASUREMENTS OF THE BELL X-5 
RESEARCH AIRPLANE AT A SWEEP ANGLE OF 
58.7°. Richard D. Banner, Robert D. Reed, and 
William L. Marcy. April 1955. 22p. diagrs., 
photo., tab. (NACA RM H55A11) 



AERODYNAMICS OF A RECTANGULAR WING OF 
INFINITE ASPECT RATIO AT HIGH ANGLES OF 
ATTACK AND SUPERSONIC SPEEDS. John C. 
Martin and Frank S. Malvestuto, Jr. July 1955. 
114p. diagrs., tab. (NACA TN 3421) 



AN ANALYSIS OF ACCELERATION, AIRSPEED, 
AND GUST-VELOCITY DATA FROM ONE TYPE OF 
FOUR-ENGINE TRANSPORT AIRPLANE OPERATED 
OVER TWO DOMESTIC ROUTES. Martin R. Copp 
and Thomas L. Coleman. October 1955. 29p. 

diagrs., tabs. (NACA TN 3475) 



A PRELIMINARY INVESTIGATION OF THE EF- 
FECTS OF FREQUENCY AND AMPLITUDE ON THE 
ROLLING DERIVATIVES OF AN UNSWEPT-WTNG 
MODEL OSCILLATING IN ROLL. Lewis R. Fisher, 
Jacob H. Lichtenstein, and {Catherine D. Williams. 
January 1956. 29p. diagrs., photos. 
(NACA TN 3554) 



158 



(4) AIRCRAFT LOADS AND CONSTRUCTION 



INTERIM REPORT ON FATIGUE CHARACTERISTICS 
OF A TYPICAL METAL WING. J. L. Kepert and 
A. 0. Payne. March 1956. 80p. diagrs., photos., 
tabs. (NACA TM 1397. Originally issued as Report 
ARL/SM. 207, Aeronautical Research Laboratories, 
Australia) 



(4. 1. 1. I. 3) 
Gust Loads 



THE VARIATION OF ATMOSPHERIC TURBULENCE 
WITH ALTITUDE AND ITS EFFECT ON AIRPLANE 
GUST LOADS. Robert L. McDougal, Thomas L. 
Coleman and Philip L. Smith. November 1953. 16p. 
diagrs., 2 tabs. (NACA RM L53G15a) 



SOME DESIGN CONSIDERATIONS PERTINENT TO 
THE ROUGH -AIR BEHAVIOR OF AIRPLANES AT 
LOW ALTITUDE. Philip Donely and Clarence L. 
Gillis. November 1953. 21p. diagrs., tabs. 
(NACA RM L53J01b) 



STRUCTURAL RESPONSE TO DISCRETE AND 
CONTINUOUS GUSTS OF AN AIRPLANE HAVING 
WING -BENDING FLEXIBILITY AND A CORRELA- 
TION OF CALCULATED AND FLIGHT RESULTS. 
John C. Houbolt and Eldon E. Kordes. 1954. ii, 
22p. diagrs., 4 tabs. (NACA Rept. 1181. Formerly 
TN 3006) 



A REVISED GUST -LOAD FORMULA AND A RE- 
EVALUATION OF V-G DATA TAKEN ON CIVIL 
TRANSPORT AIRPLANES FROM 1933 TO 1950. 
Kermit G. Pratt and Walter G. Walker. 1954. ii, 
9p. diagrs., tabs. (NACA Rept. 1206. Supersedes 
TN 2964; TN 3041) 



METEOROLOGICAL PROBLEMS ASSOCIATED 
WITH COMMERCIAL TUBOJET-AIRCRAFT OPER- 
ATION. A working group of the NACA Subcommittee 
on Meteorological Problems. June 1955. 46p. 
(NACA RM 54L29) 



A REEVALUATION OF GUST -LOAD STATISTICS 
FOR APPLICATIONS IN SPECTRAL CALCULA- 
TIONS. Harry Press and May T. Meadows. 
August 1955, 19p. diagrs. (NACA TN 3540) 



AN ANALYSIS OF ACCELERATION, AIRSPEED, 
AND GUST-VELOCITY DATA FROM A FOUR- 
ENGINE TRANSPORT AIRPLANE IN OPERATIONS 
ON AN EASTERN UNITED STATES ROUTE. 
Thomas L. Coleman and Mary W. Fetner. September 
1955. 20p. diagrs., 3 tabs. (NACA TN 3483) 



AN ANALYSIS OF ACCELERATION, AIRSPEED, 
AND GUST -VELOCITY DATA FROM ONE TYPE OF 
FOUR-ENGINE TRANSPORT AIRPLANE OPERATED 
OVER TWO DOMESTIC ROUTES. Martin R. Copp 
and Thomas L. Coleman. October 1955. 29p. 

diagrs., tabs. (NACA TN 3475) 



SUMMARY OF DERIVED GUST VELOCITIES OB- 
TAINED FROM MEASUREMENTS WITHIN THUN- 
DERSTORMS. H(arold) B. Tolefson. October 
1955. 19p. diagrs., tabs. (NACA TN 3538) 



THE PROBLEM OF REDUCING THE SPEED OF A 
JET TRANSPORT IN FLIGHT. Don D. Davis, Jr. 
December 1955. 22p. diagrs. (NACA TN 3613) 



GUST -LOAD AND AIRSPEED DATA FROM ONE 
TYPE OF TWO-ENGINE AIRPLANE ON SDC CIVIL 
AIRLINE ROUTES FROM 1947 TO 1955. Walter G. 
Walker. February 1956. 25p. diagrs., tabs. 
(NACA TN 3621) 



SUMMARY OF LOCATIONS AND EXTENTS OF TUR- 
BULENT AREAS ENCOUNTERED DURING FLIGHT 
INVESTIGATIONS OF THE JET STREAM FROM 
OCTOBER 1953 TO MAY 1954 AND NOVEMBER 1954 
TO JULY 1955. Mary W. Fetner. April 1956. 
lOp. tab. (NACA RM L55H04a) 



APPROXIMATE INDICIAL LIFT FUNCTIONS FOR 
SEVERAL WINGS OF FINITE SPAN IN INCOM- 
PRESSIBLE FLOW AS OBTAINED FROM OSCILLA- 
TORY LIFT COEFFICIENTS. Joseph A. Drischler. 
May 1956. 26p. diagrs., tab. (NACA TN 3639) 



AN INVESTIGATION OF FORWARD-LOCATED 
FKED SPOILERS AND DEFLECTORS AS GUST 
ALLEVIATORS ON AN UNSWEPT-WING MODEL. 
Delwin R. Croom, C. C. Shufflebarger, and 
Jarrett K. Huffman. June 1956. 26p. diagrs., 
photo. (NACA TN 3705) 



(4. 1.1. 1.4) 
Buffeting Loads 



MEASUREMENT AND ANALYSIS OF WING AND 
TAIL BUFFETING LOADS ON A FIGHTER AIR- 
PLANE. Wilber B. Huston and T. H. Skopinski. 
1955. i, 27p. diagrs., photo., tabs. (NACA Rept. 
1219. Supersedes TN 3080) 



MEASUREMENT OF AERODYNAMIC FORCES FOR 
VARIOUS MEAN ANGLES OF ATTACK ON AN AIR- 
FOIL OSCILLATING IN PITCH AND ON TWO 
FINITE-SPAN WINGS OSCILLATING IN BENDING 
WITH EMPHASIS ON DAMPING IN THE STALL. 
A. Gerald Rainey. May 1956. i, 66p. diagrs., 
photo. (NACA TN 3643) 



(4. 1. 1. 2) 
TAIL 



PRELIMINARY RESULTS OF HORIZONTAL -TAIL 
LOAD MEASUREMENTS OF THE BELL X-5 RE- 
SEARCH AIRPLANE. John T. Rogers and Angel H. 
Dunn. August 15, 1952. 22p. diagrs., photos., 
tabs. (NACA RM L52G14) 



159 



(4) AIRCRAFT LOADS AND CONSTRUCTION 



LONGITUDINAL FLIGHT CHARACTERISTICS OF 
THE BELL X-5 RESEARCH AIRPLANE AT 59° 
SWEEPBACK WITH MODIFIED WING ROOTS. 
James A. Martin. August 1953. 25p. diagrs., 
photos,, tab. (NACA RM L53E28) 



EFFECTS OF WING POSITION AND FUSELAGE 
SIZE ON THE LOW-SPEED STATIC AND ROLLING 
STABILITY CHARACTERISTICS OF A DELTA-WING 
MODEL. Alex Goodman and David F. Thomas, Jr. 
1955. ii, 31p. diagrs., photos., tabs. 
(NACA Rept. 1224. Supersedes TN 3063) 



VORTEX INTERFERENCE ON SLENDER AIR- 
PLANES. Alvin H. Sacks. November 1955. 
diagr. (NACA TN 3525) 



19p, 



DETERMINATION OF VORTEX PATHS BY SERIES 
EXPANSION TECHNIQUE WITH APPLICATION TO 
CRUCIFORM WINGS. Alberta Y. Alksne. 
April 1956. 40p. diagrs., photos. (NACA TN 3670) 



(4. 1. 1.2. 1) 

Steady L.oads 



PRELIMINARY RESULTS OF HORIZONTAL -TAIL 
LOAD MEASUREMENTS OF THE BELL X-5 RE- 
SEARCH AIRPLANE, John T. Rogers and Angel H, 
Dunn. August 15, 1952. 22p. diagrs., photos., 
tabs. (NACA RM L52G14) 



AN EXPERIMENTAL AND THEORETICAL INVES- 
TIGATION AT HIGH SUBSONIC SPEEDS OF THE 
EFFECTS OF HORIZONTAL-TAIL HEIGHT ON THE 
AERODYNAMIC CHARACTERISTICS IN SIDESLIP 
OF AN UNSWEPT, UNTAPERED TAIL ASSEMBLY. 
Harleth G. Wiley and Donald R. Riley. December 
1953. 71p. diagrs., tab. (NACA RM L53J19) 



THE EFFECT OF BLUNT-TRAILING-EDGE MODI- 
FICATIONS ON THE HIGH-SPEED STABILITY AND 
CONTROL CHARACTERISTICS OF A SWEPT -WING 
FIGHTER AIRPLANE. Melvin Sadoff, Frederick H. 
Matteson, and Rudolph D. Van Dyke, Jr. May 1954. 
55p. diagrs., photos., tab. (NACA RM A54C31) 

FLIGHT MEASUREMENTS OF HORIZONTAL-TAIL 
LOADS ON THE BELL X-5 RESEARCH AIRPLANE 
AT A SWEEP ANGLE OF 58.7°. Robert D. Reed. 
July 1955. 19p. diagrs., photo., tab. 
(NACA RM H55E20a) 



(4. 1.1.2.2) 

Maneuvering 



EFFECT OF FORMATION POSITION ON LOAD 
FACTORS OBTAINED ON F2H AIRPLANES. Carl R. 
Huss and Harold A. Hamer. December 1951. 15p. 
diagrs., 3 tabs. (NACA RM L51I05) 



TIME HISTORIES OF MANEUVERS PERFORMED 
WITH AN F-86A AIRPLANE DURING SQUADRON 
OPERATIONS. Harold A. Hamer and Campbell 
Henderson. February 1952. 90p. diagrs., 3 tabs. 

(NACARM L51K30) 



AILERON AND ELEVATOR HINGE MOMENTS OF 
THE BELL X-l AIRPLANE MEASURED IN TRAN- 
SONIC FLIGHT. Hubert M. Drake and John B. 
McKay. June 1953. 27p. diagrs. 
(NACA RM L53E04) 



A FLIGHT EVALUATION OF THE LONGITUDINAL 
STABILITY CHARACTERISTICS ASSOCIATED WITH 
THE PITCH-UP OF A SWEPT -WING AIRPLANE IN 
MANEUVERING FLIGHT AT TRANSONIC SPEEDS. 
Seth B. Anderson and Richard S. Bray. 1955. ii, 
12p. diagrs., photo., tab. (NACA Rept. 1237. 
Supersedes RM A51I12) 



ANALYSIS OF THE HORIZONTAL -TAIL LOADS 
MEASURED IN FLIGHT ON A MULTIENGINE JET 
BOMBER. William S. Aiken, Jr. and Bernard 
Wiener. September 1955. i, 69p. diagrs., photo., 
6 tabs. (NACA TN 3479) 



A PRELIMINARY INVESTIGATION OF THE EF- 
FECTS OF FREQUENCY AND AMPLITUDE ON THE 
ROLLING DERIVATIVES OF AN UNSWEPT -WING 
MODEL OSCILLATING IN ROLL. Lewis R. Fisher, 
Jacob H. Lichtenstein, and Katherine D. Williams. 
January 1956. 29p. diagrs., photos. 
(NACA TN 3554) 



(4. 1. 1.2.3) 

Buffeting and Gust 



LOW-LIFT BUFFET CHARACTERISTICS OB- 
TAINED FROM FLIGHT TESTS OF UNSWEPT THIN 
INTERSECTING SURFACES AND OF THICK 35° 
SWEPTBACK SURFACES. Homer P. Mason. 
January 1953. 21p. diagrs., photos. (NACA 
RM L52H12) 



LONGITUDINAL FLIGHT CHARACTERISTICS OF 
THE BELL X-5 RESEARCH AIRPLANE AT 59° 
SWEEPBACK WITH MODIFIED WING ROOTS. 
James A. Martin. August 1953. 25p. diagrs., 
photos., tab. (NACA RM L53E28) 



MEASUREMENTS OF NORMAL-FORCE- 
COEFFICIENT FLUCTUATION ON FOUR 9- 
PERCENT-THICK AIRFOILS HAVING DIFFERENT 
LOCATIONS OF MAXIMUM THICKNESS. Milton D. 
Humphreys. April 1954. 21p. diagrs., photos. 
(NACA RM L54B22) 

FLIGHT DETERMINATION OF THE BUFFETING 
CHARACTERISTICS OF THE BELL X-5 RESEARCH 
AIRPLANE AT 58.7° SWEEPBACK. Donald W. 

Briggs. May 1954. 31p. diagrs., photo., tabs. 
(NACA RM L54C17) 



MEASUREMENT AND ANALYSIS OF WING AND 
TAIL BUFFETING LOADS ON A FIGHTER AIR- 
PLANE. Wilber B. Huston and T. H. Skopinski. 
1955. i, 27p. diagrs., photo., tabs. (NACA Rept. 
1219. Supersedes TN 3080) 



160 



(4) AIRCRAFT LOADS AND CONSTRUCTION 



(4. 1. 1. 3) 

FUSELAGE, NACELLES, AND 

CANOPIES 



AERODYNAMIC CHARACTERISTICS OF NACA RM- 

10 MISSILE IN 8- BY 6-FOOT SUPERSONIC WIND 
TUNNEL AT MACH NUMBERS FROM 1.49 TO 1.98. 

11 - PRESENTATION AND ANALYSIS OF FORCE 
MEASUREMENTS. Fred T, Esenwein, Leonard J. 
Obery, and Carl F. Schueller. July 21, 1950. 34p 
diagrs., photo. (NACA RM E50D28) 



AERODYNAMIC CHARACTERISTICS OF NACA 
RM-10 MISSILE IN 8- BY 6-FOOT SUPERSONIC 
WIND TUNNEL AT MACH NUMBERS FROM 1.49 TO 
1.98. HI - ANALYSIS OF FORCE DISTRIBUTION 
AT ANGLE OF ATTACK (STABILIZING FINS RE- 
MOVED). Roger W, Luidens and Paul C. Simon. 
December 12, 1950. 26p. diagrs. 
(NACA RM E50I19) 



AERODYNAMIC CHARACTERISTICS INCLUDING 
PRESSURE DISTRIBUTIONS OF A FUSELAGE AND 
THREE COMBINATIONS OF THE FUSELAGE WITH 
SWEPT-BACK WINGS AT HIGH SUBSONIC SPEEDS. 
Fred B. Sutton and Andrew Martin. February 6, 
1951. 117p. diagrs., photos., tabs. 
(NACA RM A50J26a) 



AERODYNAMIC CHARACTERISTICS OF THE NACA 
RM-10 RESEARCH MISSILE IN THE AMES 1- BY 
3-FOOT SUPERSONIC WIND TUNNEL NO. 2 - 
PRESSURE AND FORCE MEASUREMENTS AT 
MACH NUMBERS OF 1.52 AND 1.98. Edward W. 
Perkins, Forrest E. Gowen and Leland H. Jorgensen. 
September 1951. 37p. diagrs. (NACA RM A51G13) 



TRANSONIC -WING INVESTIGATION IN THE 
LANGLEY 8-FOOT HIGH-SPEED TUNNEL AT HIGH 
SUBSONIC MACH NUMBERS AND AT A MACH NUM- 
BER OF 1.2. ANALYSIS OF PRESSURE DISTRIBU- 
TION OF WING-FUSELAGE CONFIGURATION HAV- 
ING A WING OF 45° SWEEPBACK, ASPECT RATIO 
4, TAPER RATIO 0.6, AND NACA 65A006 AIRFOIL 
SECTION. Donald L. Loving and Bruce B. 
Estabrooks. September 1951. 132p. diagrs., photos. 
(NACARM L51F07) 



INVESTIGATION OF THE EFFECT OF A NACELLE 
AT VARIOUS CHORDWISE AND VERTICAL POSI- 
TIONS ON THE AERODYNAMIC CHARACTERISTICS 
AT HIGH SUBSONIC SPEEDS OF A 45° SWEPTBACK 
WING WITH AND WITHOUT A FUSELAGE. 
H. Norman Silvers, Thomas J. King, Jr., and 
Thomas B. Pasteur, Jr. September 1951. 71p. 
diagrs., photos., 3 tabs. (NACA RM L51H16) 



PRESSURE MEASUREMENTS ON A BODY OF REVO- 
LUTION IN THE LANGLEY 16 -FOOT TRANSONIC 
TUNNEL AND A COMPARISON WITH FREE-FALL 
DATA. Joseph M. Hallissy, Jr. March 1952. 19p. 
diagrs. (NACA RM L5lL07a) 



PRESSURE DISTRIBUTIONS AT MACH NUMBERS 
FROM 0.6 TO 1.9 MEASURED IN FREE FLIGHT ON 
A PARABOLIC BODY OF REVOLUTION WITH 
SHARPLY CONVERGENT AFTERBODY. William E. 
Stoney, Jr. April 1952. 34p. diagrs., photos. 
(NACA RM L51L03) 



TRANSONIC DRAG CHARACTERISTICS AND PRES- 
SURE DISTRIBUTION ON THE BODY OF A WING- 
BODY COMBINATION CONSISTING OF A BODY OF 
REVOLUTION OF FINENESS RATIO 12 AND A WING 
HAVING SWEEPBACK OF 45°, ASPECT RATIO 4, 
TAPER RATIO 0.6, AND NACA 65A006 AIRFOIL 
SECTIONS. Max C Kurbjun and Jim Rogers 
Thompson. April 1952. 28p. diagrs.. photo., tabs. 
(NACA RM L52B12) 



AN ANALYSIS OF THE PRESSURE DISTRIBUTION 
MEASURED ON A BODY OF REVOLUTION AT 
TRANSONIC SPEEDS IN THE SLOTTED TEST SEC- 
TION OF THE LANGLEY 8-FOOT TRANSONIC 
TUNNEL. Bruce B. Estabrooks. June 1952. 42p. 
diagrs. (NACA RM L52D21a) 



PRESSURE DISTRIBUTION AND PRESSURE DRAG 
FOR A HEMISPHERICAL NOSE AT MACH NUM- 
BERS 2.05. 2.54. AND 3.04. Leo T. Chauvin. 
December 1952. 14p. diagrs., photos. 
(NACA RM L52K06) 



PRESSURE AND FORCE CHARACTERISTICS AT 
TRANSONIC SPEEDS OF A SUBMERGED 
DIVERGENT- WALLED AIR INLET ON A BODY OF 
REVOLUTION. John A. Braden and P. Kenneth 
Pierpont. May 1953. 65p. photos., diagrs., tabs. 
(NACA RM L53C13) 



DISTRIBUTION OF LIFT AND PITCHING MOMENT 
BETWEEN WING AND FUSELAGE AND EFFECTS 
OF WING FLEXIBILITY AND DIVE BRAKE ON A 
1 30-SCALE SEMISPAN MODEL OF THE EELL X-5 
AIRPLANE AT TRANSONIC SPEEDS AS DETER- 
MINED SY THE NACA WING-FLOW METHOD. 
Garland J. Morris and Norman S. Silsby. March 
1954. 46p. diagrs., photos., tab. 
(NACA RM L54A11) 



SOME INTERNAL-FLOW CHARACTERISTICS AT 
ZERO FLIGHT SPEED OF AN ANNULAR SUPER- 
SONIC INLET AND AN OPEN-NOSE INLET WITH 
SHARP AND ROUNDED LIPS. Joseph R. Milillo. 
July 1954. 23p. diagrs., photo. 
(NACA RM L54E19} 



COMPARISON OF EXPERIMENTAL AND THEO- 
RETICAL NORMAL- FORCE DISTRIBUTIONS (IN- 
CLUDING REYNOLDS NUMBER EFFECTS) ON AN 
OGPVE -CYLINDER BODY AT MACH NUMBER 1.98. 
Edward W. Perkins and Leland H. Jorgensen. May 
1956. 50p. diagrs., tab. (NACA TN 3716. Super- 
sedes RM A54H23) 



(4. 1. 1.4) 
ROTATING WINGS 



GUST-TUNNEL INVESTIGATION OF THE EFFECT 
OF A SHARP-EDGE GUST ON THE FLAPWISE 
BLADE BENDING MOMENTS OF A MODEL HELI- 
COPTER ROTOR. Domenic J. Maglieri and Thomas 
D. Reisert. August 1955. 24p. diagrs., photos. 
(NACA TN 3470) 



161 



(4) AIRCRAFT LOADS AND CONSTRUCTION 



(4. 1. 1.5) 
AEROELASTICITY 



AERODYNAMIC CHARACTERISTICS INCLUDING 
PRESSURE DISTRIBUTIONS OF A FUSELAGE AND 
THREE COMBINATIONS OF THE FUSELAGE WITH 
SWEPT-BACK WINGS AT HIGH SUBSONIC SPEEDS. 
Fred B. Sutton and Andrew Martin. February 6, 
1951. 11 7p. diagrs., photos., tabs. 
(NACA RM A50J26a) 



EXPERIMENTAL INVESTIGATION OF THE OSCIL- 
LATING FORCES AND MOMENTS ON A TWO- 
DIMENSIONAL WING EQUIPPED WITH AN OSCIL- 
LATING CIRCULAR-ARC SPOILER. Sherman A. 
Clevenson and John E. Tomassoni. January 1954. 
20p. diagrs., photos. (NACA RM L53K18) 



DISTRIBUTION OF LIFT AND PITCHING MOMENT 
BETWEEN WING AND FUSELAGE AND EFFECTS 
OF WING FLEXIBILITY AND DIVE BRAKE ON A 
1/30 -SCALE SEMISPAN MODEL OF THE BELL X-5 
AIRPLANE AT TRANSONIC SPEEDS AS DETER- 
MINED BY THE NACA WING-FLOW METHOD. 
Garland T Morris and Norman S. Silsby. March 
1054. 4Gp. diagrs., photos., tab. 
(XACARM L54A11) 



COMPARISON BETWEEN THEORETICAL AND EX- 
PERIMENTAL RATES OF ROLL OF TWO MODELS 
WITH FLEXIBLE RECTANGULAR WINGS AT SU- 
PERSONIC SPEEDS. John M. Hedgepeth and 
Robert J. Kell. August 1954. 21p. diagrs., photo., 
tabs. (NACA RM L54F23) 



MEASUREMENT AND ANALYSIS OF WING AND 
TAIL BUFFETING LOADS ON A FIGHTER AIR- 
PLANE. Wilber B. Huston and T. H. Skopinski. 
1955. i, 27p. diagrs., photo., tabs. (NACA Rept. 
1219. Supersedes TN 3080) 



GENERALIZED INDICIAL FORCES ON DEFORMING 
RECTANGULAR WINGS IN SUPERSONIC FLIGHT. 
Harvard Lomax, Franklyn B. Fuller and Loma 
Sluder. 1955. ii, 27p. diagrs., tab. 
(NACA Rept. 1230. Supersedes TN 3286) 



PRELIMINARY STUDY OF SOME FACTORS WHICH 
AFFECT THE STALL-FLUTTER CHARACTER- 
ISTICS OF THTN WINGS. A. Gerald Rainey. March 
1956. 33p. diagrs., photo., tab. (NACA TN 3622. 
Supersedes RM L52D08) 



ON PANEL FLUTTER AND DIVERGENCE OF INFI- 
NITELY LONG UNSTIFFENED AND RING- 
STIFFENED THIN-WALLED CIRCULAR CYLINDERS. 
Robert W. Leonard and John M. Hedgepeth. April 
1956. 52p. diagrs. (NACA TN 3638) 



(4.1.2) 
LANDING 



(4. 1. 2. 1) 
IMPACT 



STATISTICAL MEASUREMENTS OF CONTACT 
CONDITIONS OF 478 TRANSPORT -AIRPLANE 
LANDINGS DURING ROUTINE DAYTIME OPERA- 
TIONS. Norman S. Silsby. 1955. ii, 17p. diagrs., 
photos., tabs. (NACA Rept. 1214. Supersedes 
TN 3194) 



COMPARISON OF LANDING-IMPACT VELOCITIES 
OF FIRST AND SECOND WHEEL TO CONTACT 
FROM STATISTICAL MEASUREMENTS OF TRANS- 
PORT AIRPLANE LANDINGS. Eziaslav N. Harrin. 
February 1956. 22p. diagrs., photo., tabs. 
(NACA TN 3610) 



(4.1.2.1.1) 

Land 



VERTICAL AND DRAG GROUND-REACTION 
FORCES DEVELOPED IN LANDING IMPACTS OF A 
LARGE AIRPLANE. Richard H. Sawyer, Albert W. 
Hall and James M. McKay. June 1955. 12p. diagrs. 
(NACARM L55E12c) 



EFFECT OF INTERACTION ON LANDING-GEAR 
BEHAVIOR AND DYNAMIC LOADS IN A FLEXIBLE 
AIRPLANE STRUCTURE. Francis E. Cook and 
Benjamin Milwitzky. August 1955. 75p. diagrs., 
2 tabs. (NACA TN 3467) 



FRICTION STUDY OF AIRCRAFT TIRE MATERIAL 
ON CONCRETE. W. G. Hample, Boeing Airplane 
Company. September 1955. 34p. diagrs., photos. 
(NACA TN 3294) 



A METHOD FOR OBTAINING STATISTICAL DATA 
ON AIRPLANE VERTICAL VELOCITY AT GROUND 
CONTACT FROM MEASUREMENTS OF CENTER- 
OF-GRAVITY ACCELERATION. Robert C. Dreher. 
February 1956. 21p. diagrs., photo., tabs. 
(NACA TN 3541) 



(4. 1. 2. 1.2) 

Water 

WATER LANDING INVESTIGATION OF A HYDRO- 
SKI MODEL AT BEAM LOADINGS OF 18.9 AND 4.4. 
Sidney A. Batterson. September 1951. 54p. 
diagrs., photos., tab. (NACA RM L51F27) 



162 



(4) AIRCRAFT LOADS AND CONSTRUCTION 



ESTIMATION OF WATER LANDING LOADS ON 
HYDRO-SKI-EQUIPPED AIRCRAFT. Emanuel 
Schnitzer. July 1953. 14p. diagrs. 
(NACA RM L53D29) 



(4. 1. 2. 2) 
GROUND-RUN 



EFFECT OF CARRIAGE MASS UPON THE LOADS 
AND MOTIONS OF A PRISMATIC BODY DURING 
HYDRODYNAMIC IMPACT. Melvin F. Markey. 
March 1956. 45p. diagrs. (NACA TN 3619) 

ON SPECTRAL ANALYSIS OF RUNvVAY ROUGHNESS 
AND LOADS DEVELOPED DURING TAXIING. John 
C. Houbolt, James H. Walls and Robert F. Smiley. 
July 1955. 9p. diagrs. (NACA TN 3484) 



PRELIMINARY PERFORMANCE DATA OF SEVERAL 
TAIL-PIPE-CASCADE-TYPE MODEL THRUST 
REVERSERS. James G. Henzel, Jr. and Jack G. 
McArdle. August 1955. 48p. diagrs., photos., tab. 
(NACA RM E55F09) 



(4. 1. 2. 2. 1) 

Land 

REDUCTION OF THE SHIMMY TENDENCY OF TAIL 
AND NOSE-WHEEL LANDING GEARS BY INSTAL- 
LATION OF SPECLALLY DESIGNED TIRES. 

(Verminderung der Flatterneigung von Sporn- und 
Bugwerken durch Einbau besonders geformter 
Reifen). H. Schrode. July 1955. 13p. diagrs. 
(NACA TM 1391. Trans, from Deutschen 
Versuchsanstalt fur Luftfahrt E. V., Berlin- 
Adlershof. Technische Berichte, v. 10, 1943, 
p. 113-116) 



FRICTION STUDY OF AIRCRAFT TIRE MATERIAL 
ON CONCRETE. W. G. Hample, Boeing Airplane 
Company, September 1955. 34p. diagrs., photos. 
(NACA TN 3294) 

LOW-SPEED YAWED-ROLLING CHARACTERISTICS 
AND OTHER ELASTIC PROPERTIES OF A PAIR OF 
26-INCH-DIAMETER, 12-PLY-RATING, TYPE VII 
AIRCRAFT TIRES. Walter B. Home, Robert F. 
Smiley, and Bertrand H. Stephenson. May 1956. 
98p. diagrs., photos., tabs. (NACA TN 3604) 



CORRELATION, EVALUATION, AND EXTENSION 
OF LINEARIZED THEORIES FOR TIRE MOTION 
AND WHEEL SHIMMY. Robert F. Smiley. 
June 1956. iv, 139p. diagrs., tab. (NACA TN 3632) 



(4. 1. 2. 2. 2) 
Water 



PRELIMINARY INVESTIGATION OF SELF- 
EXCITED VIBRATIONS OF SINGLE PLANING 
SURFACES. Elmo J. Mottard. June 1956. 19p. 
diagrs., photos., tab. (NACA TN 3698. Supersedes 
RM L55J27) 



163 



(4) AIRCRAFT LOADS AND CONSTRUCTION 



(4.2) 
Vibration and Flutter 



PRELIMINARY FLIGHT INVESTIGATION OF THE 
MANEUVERING ACCELERATIONS AND BUFFET 
BOUNDARY OF A 35° SWEPT -WING AIRPLANE AT 
HIGH ALTITUDE AND TRANSONIC SPEEDS. 
George A. Rathert, Jr., Howard L. Ziff, and George 
E. Cooper. February 21, 1951. 12p. diagrs., 
photo., tab. (NACA RM A50L04) 



SOME EXPERIMENTS ON THE FLUTTER OF 
SWEPTBACK CANTILEVER WING MODELS AT 
MACH NUMBER 1.3. W. J. Tuovila. March 15, 
1951. lOp. diagrs., tab. (NACA RM L51A11) 



NOTES ON LOW-LIFT BUFFETING AND WING 
DROPPING AT MACH NUMBERS NEAR 1. Paul E. 
Purser. March 16, 1951, 22p. diagrs., tab. 
(NACA RM L51A30) 



REVIEW OF SOME RECENT DATA ON BUFFET 
BOUNDARIES. Paul E. Purser and John A. Wyss. 
May 23, 1951. lip. diagrs. (NACA RM L51E02a) 



SOME WIND-TUNNEL RESULTS OF AN INVESTIGA- 
TION OF THE FLUTTER OF SWEPTBACK- AND 
TRIANGULAR -WING MODELS AT MACH NUMBER 
1.3. W. J. Tuovila. May 1952. 12p. diagrs., tab. 
(NACA RM L52C13) 



SOME EXPERIMENTAL STUDIES OF PANEL 
FLUTTER AT MACH NUMBER 1.3. Maurice A. 
Sylvester and John E. BaUcr. December 1952. 
25p. diagrs., photos., tab. (NACA RM L52I16) 



LOW-LIFT BUFFET CHARACTERISTICS OB- 
TAINED FROM FLIGHT TESTS OF UNSWEPT THIN 
INTERSECTING SURFACES AND OF THICK 35° 
SWEPTBACK SURFACES. Homer P. Mason. 
January 1953. 21p. diagrs.. photos. (NACA 
RM L52H12) 



SUPERSONIC FLOW PAST OSCILLATING AIRFOILS 
INCLUDING NONLINEAR THICKNESS EFFECTS. 
Milton D. Van Dyke. 1954. ii, 17p. diagrs. (NACA 
Rept. 1183. Formerly TN 2982) 



EXPERIMENTAL INVESTIGATION OF THE OSCIL- 
LATING FORCES AND MOMENTS ON A TWO- 
DIMENSIONAL WING EQUIPPED WITH AN OSCIL- 
LATING CIRCULAR-ARC SPOILER. Sherman A. 
Clevenson and John E. Tomassoni. January 1954. 
20p. diagrs., photos. (NACA RM L53K18) 



SUMMARY OF RECENT THEORETICAL AND 
EXPERIMENTAL WORK ON BOX-BEAM VIBRA- 
TIONS. John M. Hedgepeth. June 1955. lOp. 
diagrs., photo., 2 tabs. (NACA RM L55E09a) 



BEHAVIOR OF A CANTILEVER PLATE UNDER 
RAPID-HEATING CONDITIONS. Louis F. Vosteen 
and Kenneth E. Fuller. July 1955. 17p. diagrs. 
(NACA RM L55E20C) 



SOME EFFECTS OF FLUID IN PYLON-MOUNTED 
TANKS ON FLUTTER. James R. Reese. July 1955. 
7p. diagrs., tab. (NACA RM L55F10) 



THEORETICAL INVESTIGATION OF FLUTTER OF 
TWO-DIMENSIONAL FLAT PANELS WITH ONE 
SURFACE EXPOSED TO SUPERSONIC POTENTIAL 
FLOW. Herbert C. Nelson and Herbert J. 
Cunningham. July 1955. 60p. diagrs., tab. (NACA 
TN 3465) 



INVESTIGATION OF THE VIBRATIONS OF A HOL- 
LOW THIN-WALLED RECTANGULAR BEAM. 
Eldon E. Kordes and Edwin T. Kruszewski. October 
1955. 24p. diagrs., photos., 2 tabs. (NACA 
TN 3463) 



INFLUENCE OF SHEAR DEFORMATION ON THE 
CROSS SECTION ON TORSIONAL FREQUENCIES 
OF BOX BEAMS. Edwin T. Kruszewski and William 
W. Davenport. October 1955. 23p. diagrs. (NACA 
TN 3464) 



TABULATION OF THE f x FUNCTIONS WHICH 
OCCUR IN THE AERODYNAMIC THEORY OF 
OSCILLATING WINGS IN SUPERSONIC FLOW. 

Vera Huckel. February 1956. 59p. tab. 
(NACATN 3606) 



EXPERIMENTAL INVESTIGATION OF THE VIBRA- 
TIONS OF A BUILT-UP RECTANGULAR BOX 
BEAM. Eldon E. Kordes and Edwin T. Kruszewski. 
February 1956. 28p. diagrs., photos., tabs. 
(NACATN 3618) 



THE ACCURACY OF THE SUBSTITUTE -STRINGER 
APPROACH FOR DETERMINING THE BENDING 
FREQUENCIES OF MULTISTRINGER BOX BEAMS. 
William W. Davenport. April 1956. 28p. diagrs., 
tab. (NACA TN 3636) 



INFLUENCE OF LARGE AMPLITUDES ON FLEX- 
URAL MOTIONS OF ELASTIC PLATES. George 
Herrmann, Columbia University. May 1956. 45p. 
diagrs. (NACA TN 3578) 



MEASUREMENT OF AERODYNAMIC FORCES FOR 
VARIOUS MEAN ANGLES OF ATTACK ON AN AIR- 
FOIL OSCILLATING IN PITCH AND ON TWO 
FINITE -SPAN WINGS OSCILLATING IN BENDING 
WITH EMPHASIS ON DAMPING IN THE STALL. 
A. Gerald Rainey. May 1956. i, 66p. diagrs., 
photo. (NACA TN 3643) 



EXPERIMENTAL MEASUREMENTS OF FORCES 
AND MOMENTS ON A TWO-DIMENSIONAL OSCIL- 
LATING WING AT SUBSONIC SPEEDS. Sherman A, 
Clevenson and Edward Widmayer, Jr. June 1956. 
28p. diagrs., tab. (NACA TN 3686. Supersedes 
RM L9K28a) 



164 



(4) AIRCRAFT LOADS AND CONSTRUCTION 



(4.2.1) 
WINGS AND AILERONS 



RESULTS OF TWO FREE-FALL EXPERIMENTS ON 
FLUTTER OF THIN UNSWEPT WINGS IN THE 
TRANSONIC SPEED RANGE. William T. Lauten, Jr., 
and Herbert C. Nelson. May 8, 1951. 26p. diagrs., 
photo., tabs. (NACA RM L51C08) 



RECENT EXPERIMENTAL FLUTTER STUDIES. 
Arthur A. Regier and Dennis J. Martin. June 12, 
1951. 18p. diagrs. (NACA RM L51F11) 



SUMMARY OF FLUTTER EXPERIENCES AS A 
GUIDE TO THE PRELIMINARY DESIGN OF LIFTING 
SURFACES ON MISSILES. Dennis J. Martin. 
November 1951. 16p. diagrs. (NACA RM L51J30) 

A PRELIMINARY WIND-TUNNEL INVESTIGATION 
OF FLUTTER CHARACTERISTICS OF DELTA 
WINGS. Robert W. Herr. April 1952. 35p. 
diagrs., tabs. (NACA RM L52B14a) 



RESULTS OF TWO EXPERIMENTS ON FLUTTER 
OF HIGH-ASPECT-RATIO SWEPT WINGS IN THE 
TRANSONIC SPEED RANGE. W. T. Lauten, Jr., 
and Burke R. O'Kelly. July 1?52. 22p. diagrs., 
photos., tabs, (NACA RML52D24b) 



FREE-FLIGHT INVESTIGATION AT ZERO LIFT IN 
THE MACH NUMBER RANGE BETWEEN 0.7 AND 
1.4 TO DETERMINE THE EFFECTIVENESS OF AN 
INSET TAB AS A MEANS OF AERODYNAMICALLY 
RELIEVING AILERON HINGE MOMENTS. William 
M. Bland, Jr., and Edward T. Marley. January 
1953. 19p. diagrs., photos. (NACA RM L52K07) 



PRELIMINARY RESULTS OF SUPERSONIC-JET 
TESTS OF SIMPLIFIED WING STRUCTURES. 
Richard R. Heldenfels and Richard Rosecrans. 
July 1953. 19p. diagrs., phutos. 
(NACA RM L53E26a) 



TEST OF AN AERODYNAMICALLY HEATED 
MULTIWEB WING STRUCTURE (MW-1) IN A FREE 
JET AT MACH NUMBER 2. Richard R. Heldenfels, 
Richard Rosecrans, and George E. Griffith. July 
1953. 37p. diagrs., photos. (NACA RM L53E27) 



FLIGHT DETERMINATION OF THE BUFFETING 
CHARACTERISTICS OF THE BELL X-5 RESEARCH 
AIRPLANE AT 58.7° SWEEPBACK. Donald W. 
Briggs. May 1954. 31p. diagrs., photo., tabs. 
(NACARM L54C17) 



MEASUREMENT AND ANALYSIS OF WING AND 
TAIL BUFFETING LOADS ON A FIGHTER AIR- 
PLANE. Wilber B. Huston and T. H. Skopinski. 
1955. i, 27p. diagrs., photo., tabs. (NACA Rept. 
1219. Supersedes TN 3080) 



GENERALIZED INDICIAL FORCES ON DEFORMING 
RECTANGULAR WINGS IN SUPERSONIC FLIGHT. 
Harvard Lomax, Franklyn B. Fuller and Loma 
Sluder. 1955. ii, 27p. diagrs., tab. 
(NACA Rept. 1230. Supersedes TN 3286) 



THEORETICAL AND EXPERIMENTAL INVESTIGA- 
TION OF THE EFFECT OF TUNNEL WALLS ON 
THE FORCES ON AN OSCILLATING AIRFOIL IN 
TWO-DIMENSIONAL SUBSONIC COMPRESSIBLE 
FLOW. Harry L. Runyan, Donald S. Woolston and 
A. Gerald Rainey. June 1955. 41p. diagrs., photo. 
(NACA TN 3416. Supersedes and extends 
RM L52I17a) 

SOME EFFECTS OF FLUID IN PYLON-MOUNTED 
TANKS ON FLUTTER. James R. Reese. July 1955. 
7p. diagrs., tab. (NACA RM L55F10) 

SOME EFFECTS OF SYSTEM NONLINEARITIES IN 
THE PROBLEM OF AIRCRAFT FLUTTER. 
Donald S. Woolston, Harry L. Runyan, and Thomas 
A. Byrdsong. October 1955. 20p. diagrs., tabs. 
(NACA TN 3539) 

PRELIMINARY STUDY OF SOME FACTORS WHICH 
AFFECT THE STALL-FLUTTER CHARACTER- 
ISTICS OF THIN WINGS. A. Gerald Rainey. March 
1956. 33p. diagrs., photo., tab. (NACA TN 3622. 
Supersedes RM L52D08) 

SOME WIND-TUNNEL EXPERIMENTS ON SINGLE- 
DEGREE-OF-FREEDOM FLUTTER OF AILERONS 
IN THE HIGH SUBSONIC SPEED RANGE. 
Sherman A. Clevenson. June 1956. 32p. diagrs., 
photo., tabs. (NACA TN 3687. Supersedes 
RM L9B08) 



(4.2.2) 
TAILS 



FLIGHT DETERMINATION OF THE BUFFETING 
CHARACTERISTICS OF THE BELL X-5 RESEARCH 
AIRPLANE AT 58.7° SWEEPBACK. Donald W. 
Briggs. May 1954. 31p. diagrs., photo., tabs. 
(NACA RM L54C17) 

MEASUREMENT AND ANALYSIS OF WING AND 
TAIL BUFFETING LOADS ON A FIGHTER AIR- 
PLANE. Wilber B. Huston and T. H. Skopinski. 
1955. i, 27p. diagrs., photo., tabs. (NACA Rept. 
1219. Supersedes TN 3080) 



(4. 2. 2. 1) 
ELEVATORS AND RUDDERS 



SOME EFFECTS OF SYSTEM NONLINEARITIES IN 
THE PROBLEM OF AIRCRAFT FLUTTER. 
Donald S. Woolston, Harry L. Runyan, and Thomas 
A. Byrdsong. October 1955. 20p. diagrs., tabs, 
(NACA TN 3539) 



(4.2.3) 
BODIES 



RECENT EXPERIMENTAL FLUTTER STUDIES. 
Arthur A. Regier and Dennis J. Martin. June 12, 
1951. 18p. diagrs. (NACA RM L51F11) 

SUMMARY OF FLUTTER EXPERIENCES AS A 
GUIDE TO THE PRELIMINARY DESIGN OF LIFTING 
SURFACES ON MISSILES. Dennis J. Martin, 
November 1951. 16p. diagrs. (NACA RM L51J30) 



165 



(4) AIRCRAFT LOADS AND CONSTRUCTION 



AN AIR-FLOW-DIRECTION PICKUP SUITABLE FOR 
TELEMETERING USE ON PILOTLESS AIRCRAFT. 
Wallace L. Ikard. March 1954. 25p. diagrs., 
photos. (NACA RM L53K16) 



SOME EFFECTS OF FLUID IN PYLON-MOUNTED 
TANKS ON FLUTTER. James R. Reese. July 1955. 
7p. diagrs., tab. (NACA RM L55F10) 



(4.2.4) 

PROPELLER, FANS, AND 

COMPRESSORS 



PRELIMINARY INVESTIGATION OF FLOW FLUC- 
TUATIONS DURING SURGE AND BLADE ROW 
STALL IN AXIAL-FLOW COMPRESSORS. Merle C 
Huppert. August 1952. 52p. diagrs., photos. 
(NACA RM E52E28) 



THE EFFECTS OF COMPRESSIBILITY ON THE 
UPWASH AT THE PROPELLER PLANES OF A 
FOUR-ENGINE TRACTOR AIRPLANE CONFIGURA- 
TION HAVING A WING WITH 40° OF SWEEPBACK 
AND AN ASPECT RATIO OF 10. Armando E. 
Lopez and Jerald K. Dickson. April 1953. 38p. 
diagrs., photos., tab. (NACA RM A53A30a) 



THE EFFECT OF BLADE-SECTION CAMBER ON 
THE STALL-FLUTTER CHARACTERISTICS OF 
THREE NACA PROPELLERS AT ZERO ADVANCE. 

Arthur E. Allis and John M. Swihart. April 1953. 
29n. diagrs., photo., tab. (NACA RM L53B17) 



A WIND-TUNNEL INVESTIGATION OF THE EF- 
FECTS OF THRUST -AXIS INCLINATION ON PRO- 
PELLER FIRST-ORDER VIBRATION. W. H. Gray, 
J. M. Hallissy, Jr., and A. R. Heath, Jr. 1954. 
ii, 37p. diagrs., photo., tab. (NACA Rept. 1205. 
Supersedes RM L50D13) 



VIBRATORY-STRESS INVESTIGATION OF SDC- 
AND EIGHT-BLADE DUAL-ROTATING PROPEL- 
LERS OPERATING AT ZERO ADVANCE. Atwood R. 
Heath, Jr. and Robert L. O'Neal. February 1955. 
26p. diagrs., photo., tabs. (NACA RM L54J28) 



PRELIMINARY STUDY OF SOME FACTORS WHICH 
AFFECT THE STALL-FLUTTER CHARACTER- 
ISTICS OF THIN WINGS. A. Gerald Rainey. March 
1956. 33p. diagrs., photo., tab. (NACA TN 3622. 
Supersedes RM L52D08) 

FLUTTER OF THIN PROPELLER BLADES, 
INCLUDING EFFECTS OF MACH NUMBER, 
STRUCTURAL DAMPING, AND VffiRA TORY-STRESS 
MEASUREMENTS NEAR THE FLUTTER 
BOUNDARIES. Harvey H. Hubbard, Marvin F. 
Burgess, and Maurice A. Sylvester. June 1956. 
25p. diagrs., tab. (NACA TN 3707) 



(4.2.5) 
ROTATING -WING AIRCRAFT 



SIMPLIFIED PROCEDURES AND CHARTS FOR THE 
RAPID ESTIMATION OF BENDING FREQUENCIES 
OF ROTATING BEAMS. Robert T. Yntema. June 
1955. ii, 90p. diagrs., 6 tabs. (NACA TN 3459. 
Supersedes and extends RM L54G02) 

GUST-TUNNEL INVESTIGATION OF THE EFFECT 
OF A SHARP-EDGE GUST ON THE FLAPWISE 
BLADE BENDING MOMENTS OF A MODEL HELI- 
COPTER ROTOR. Domenic J. Maglieri and Thomas 
D. Reisert. August 1955. 24p. diagrs., photos. 
(NACA TN 3470) 



(4.2.6) 
PANELS AND SURFACE 



COVERINGS 



ON PANEL FLUTTER AND DIVERGENCE OF INFI- 
NITELY LONG UNSTIFFENED AND RING- 
STIFFENED THIN-WALLED CIRCULAR CYLINDERS. 
Robert W. Leonard and John M. Hedgepeth. April 
1956. 52p. diagrs. (NACA TN 3638) 



166 



(4) AIRCRAFT LOADS AND CONSTRUCTION 



(4.3) 
Structures 



PRELIMINARY RESULTS Or SUPERSONIC-JET 
TESTS OF SIMPLIFIED WING STRUCTURES. 
Richard R. Heidenfels and Richard Rosecrans. 
Juiv 1953. I9p. diagrs.. photos. 
(NACA RM L53E26a) 

TEST OF AN AERODYNAMICALLY HEATED 
MULTIWEB WING STRUCTURE (MW-1) IN A FREE 
JET AT MACH NUMBER 2. Richard R. Heidenfels, 
Richard Rosecrans, and George E. Griffith. July 
1953. 37p. diagrs., photos. (NACA RM L53E27) 

TRANSIENT TEMPERATURE DISTRIBUTION IN AN 
AERODYNAMICALLY HEATED MULTIWEB WING. 
George E. Griffith. July 1953. lOp. diagrs. 
i NACA RM L53E27a) 



(4.3.1) 
COLUMNS 



DEVELOPMENT OF EQUIPMENT AND OF EXPERI- 
MENTAL TECHNIQUES FOR COLUMN CREEP 

TESTS. Sharad A. Patel, Martin Bloom, Burton 
Enckson, Alexander Chwick and N(icholas) J(oh n) 
Hoff, Polytechnic Institute of Brooklyn. September 
1955. 20p. diagrs., photos., tab. (NACA TN 3493) 

A UNIVERSAL COLUMN FORMULA FOR LOAD AT 
WHICH YIELDING STARTS. L. H. Donnell and V. C. 
Tsien, Illinois Institute of Technology. October 
1955. 48p. diagrs., photos., tab. {NACA TN 3415) 

CORRELATION OF CREEP-BUCKLING TESTS WITH 
THEORY. Sharad A. Patel, Joseph Kempner, 
Burton Erickson, and Abol H. Mobassery, Poly- 
technic Institute of Brooklyn. May 1956. 39p. 
diagrs., photos., tabs. (NACA RM 56C20) 



(4.3.3) 
PLATES 



STRESSES AND DEFLECTIONS OF A SWEPT BI- 
PLANE WING. George W. Zender and John E. 
Duberg. "August 1954. 41p. diagrs., photo., tabs. 
(NACA RML54E03a) 

INVESTIGATION OF THE COMPRESSIVE 
STRENGTH AND CREEP LIFETIME OF 2024-T3 
ALUMINUM-ALLOY PLATES AT ELEVATED TEM- 
PERATURES. Eldon E. Mathauser and William D. 
Deveikis. January 1956. 40p. diagis., photos., 
tabs. (NACA TN 3552. Supersedes RM L55Ellb) 

COMPRESSIVE CRIPPLING OF STRUCTURAL 
SECTIONS. Melvin S. Anderson. January 1956. 
31p. diagrs., tabs (NACA TN 3553) 

A METHOD FOR DEFLECTION ANALYSIS OF THIN 
LOW-ASPECT-RATIO WINGS. Manuel Stein and 
J. Lyell Sanders, Jr. June 1956. 65p. diagrs. 
(NACA TN 3640) 



(4.3.3. 1) 
FLAT 



DEVELOPMENT OF EQUIPMENT AND OF EXPERI- 
MENTAL TECHNIQUES FOR COLUMN CREEP 
TESTS. Sharad A. Patel, Martin Bloom, Burton 
Erickson, Alexander Chwick and N(icholas) J(oh n) 
Hoff, Polytechnic Institute of Brooklyn. September 
1955. 20p. diagrs., photos., tab. (NACA TN 3493) 

ANALYSIS OF STRESSES IN THE PLASTIC RANGE 
AROUND A CIRCULAR HOLE IN A PLATE SUB- 
JECTED TO UNIAXIAL TENSION. Bernard 
Budiansky and Robert J. Vidensek. October 1955. 
39p. diagrs., tabs. (NACA TN 3542) 

ON THE BUCKLING OF BARS AND PLATES IN THE 
PLASTIC RANGE. PART II. (Over het 
knikvraagstuk in het plastische gebied bij staven en 
platen. (Deei)). J. P. Benthem. March 1956. 
79p. diagrs., tabs. (NACA TM 1392. Trans, of 
Nationaal Luchtvaartlaboratorium, Amsterdam, 
Rapport S. 423, Jan. 1954) 



(4. 3. 3. 1. 1) 
Unstiffened 

BEHAVIOR OF A CANTILEVER PLATE UNDER 
RAPID-HEATING CONDITIONS. Louis F. Vosteen 
and Kenneth E. Fuller. July 1955. 17p. diagrs. 
(NACA RM L55E20c) 

CORRELATION OF CRIPPLING STRENGTH OF 
PLATE STRUCTURES WITH MATERIAL PROPER- 
TIES. Roger A. Anderson and Melvin S. Anderson. 
January 1956. 50p. diagrs., tabs. 
(NACA TN 3600) 

INFLUENCE OF LARGE AMPLITUDES ON FLEX- 
URAL MOTIONS OF ELASTIC PLATES. George 
Herrmann, Columbia University. May 1956. 45p. 
diagrs. (NACA TN 3578) 



(4. 3. 3. 1. 2) 

Stiffened 

FORMULAS FOR THE ELASTIC CONSTANTS OF 
PLATES WITH INTEGRAL WAFFLE-LIKE STIFF- 
ENING. Norris F. Dow, Charles Libove. and 
Ralph E. Hubka. 1954. ii, 24p. diagrs.. tab. 
(NACA Rept. 1195. Supersedes RM L53E13a) 

CHARTS RELATING THE COMPRESSIVE BUCKLING 
STRESS OF LONGITUDINALLY SUPPORTED 
PLATES TO THE EFFECTIVE DEFLECTIONAL AND 
ROTATIONAL STIFFNESS OF THE SUPPORTS. 
Roger A. Anderson and Joseph W. Semonian. 1954. 
ii, 19p. diagrs.. tabs. (NACA Rept. 1202. Super- 
sedes TN 2987) 



167 



(4) AIRCRAFT LOADS AND CONSTRUCTION 



SHEARING EFFECTIVENESS OF INTEGRAL 
STIFFENING. Robert F. Crawford and Charles 
Libove. June 1955. 37p. diagrs., photo., tab. 
(NACA TN 3443) 

CORRELATION OF CRIPPLING STRENGTH OF 
PLATE STRUCTURES WITH MATERIAL PROPER- 
TIES. Roger A. Anderson and Melvin S. Anderson. 
January 1956. 50p. diagrs., tabs. 
(NACA TN 3600) 



A THEORY FOR THE ELASTIC DEFLECTIONS OF 
PLATES INTEGRALLY STIFFENED ON ONE SIDE. 
Robert F. Crawford. April 1956. 21p. diagrs. 
(NACA TN 3646) 

INVESTIGATION OF THE COMPRESSIVE STRENGTH 
AND CREEP LIFETIME OF 2024-T ALUMINUM- 
ALLOY SKIN-STRINGER PANELS AT ELEVATED 
TEMPERATURES. Eldon E. Mathauser and 
William D. Deveikis. May 1956. 29p. diagrs., 
photos., tabs. (NACA TN 3647) 



SOME EFFECTS OF JOINT CONDUCTIVITY ON THE 
TEMPERATURES AND THERMAL STRESSES IN 
AERODYNAMICALLY HEATED SKIN-STIFFENER 
COMBINATIONS. George E. Griffith and 
Georgene H. Miltonberger. June 1956. 62p* diagrs. 
(NACA TN 3699) 



(4.3.4) 
BEAMS 



STRESSES AND DEFLECTIONS OF A SWEPT BI- 
PLANE WING. George W. Zender and John E. 
Duberg. August 1954. 41p. diagrs., photo., tabs. 
(NACA RML54E03a) 

SIMPLIFIED PROCEDURES AND CHARTS FOR THt 
RAPID ESTIMATION OF BENDING FREQUENCIES 
OF ROTATING BEAMS. Robert T. Yntema. June 
1955. ii, 90p. diagrs., 6 tabs. (NACA TN S459. 
Supersedes and extends RM L54GC2) 

INVESTIGATION OF THE VIBRATIONS OF A HOL- 
LOW THIN-WALLED RECTANGULAR BEAM. 
Eldon E. Kordes and Edwin T. Kruszewskt. October 
1955. 24p. diagrs., photos., 2 tabs. (NACA 
TN 3463) 



(4.3.4. 1) 

BOX 

CHARTS RELATING THE COMPRESSIVE BUCKLING 
STRESS OF LONGITUDINALLY SUPPORTED 
PLATES TO THE EFFECTIVE DEFLECTIONAL AND 
ROTATIONAL STIFFNESS OF THE SUPPORTS. 
Roger A. Anderson and Joseph W. Semonlan. 1954. 
ii, I9p. diagrs., tabs. (NACA Rept. 1202. Super- 
sedes TN 29B7) 

SUMMARY OF RECENT THEORETICAL AND 
EXPERIMENTAL WORK ON BOX-BEAM VIBRA- 
TIONS. John M. Hedgepeth. June 1955. lOp. 
diagrs., photo., 2 tabs. (NACA RM L55E09a) 

EXPERIMENTAL ANALYSIS OF MULTICELL 
WINGS BY MEANS OF PLASTIC MODELS. George 
W. Zender. June 1955. 6p. diagrs. (NACA 
RM L55E10b) 

RAPID RADIANT-HEATING TESTS OF MULTIWEB 
BEAMS. Joseph N. Kotanchik, Aldie E. Johnson, 
Jr., and Robert D. Ross September 1955.3o p . 
diagrs., photos., tab. (NACA TN 3474) 



INFLUENCE OF SHEAR DEFORMATION ON THE 
CROSS SECTION ON TORSIONAL FREQUENCIES 
OF BOX BEAMS. Edwin T. Kruszewski and William 
W. Davenport. October 1055. 23p. diagrs. (NACA 
TN 3464) 

EXPERIMENTAL INVESTIGATION OF THE VIBRA- 
TIONS OF A BUILT-UP RECTANGULAR BOX 
BEAM. Eldon E. Kordes and Edwin T. Kruszewski. 
February 1956. 28p. diagrs., photos., tabs. 
(NACATN 3618) 

ANALYSIS OF THE ULTIMATE STRENGTH AND 
OPTIMUM PROPORTIONS OF MULTIWEB WING 
STRUCTURES. B. Walter Rosen. March 1956. 
34p. diagrs., tabs. (NACA TN 3633) 

THE ACCURACY OF THE SUBSTITUTE-STRINGER 
APPROACH FOR DETERMINING THE BENDING 
FREQUENCIES OF MULTISTRINGER BOX BEAMS. 
William W. Davenport. April 1956. 28p. diagrs., 
tab. (NACA TN 3636) 

A METHOD FOR DEFLECTION ANALYSIS OF THIN 
LOW-ASPECT-RATIO WINGS. Manuel Stein and 
J. Lyell Sanders, Jr. June 1956. 65p. diagrs. 
(NACA TN 3640) 



(4.3.5) 
SHELLS 



ON THE MECHANISM OF BUCKLING OF A CIRCU- 
LAR CYLINDRICAL SHELL UNDER AXIAL COM- 
PRESSION. Y. Yoshimura. July 1955. 46p. 
diagrs., tab. (NACA TM 1390) 



(4.3.5. 1) 
CYLINDERS 



ON THE MECHANISM OF BUCKLING OF A CIRCU- 
LAR CYLINDRICAL SHELL UNDER AXIAL COM- 
PRESSION. Y. Yoshimura. July 1955. 46p. 
diagrs., tab. (NACA TM 1390) 



(4.3.5.1. 1) 
Circular 

ON THE MECHANISM OF BUCKLING OF A CIRCU- 
LAR CYLINDRICAL SHELL UNDER AXIAL COM- 
PRESSION. Y. Yoshimura. July 1955. 46p. 
diagrs., tab. (NACA TM 1390) 

TABLES OF COEFFICIENTS FOR THE ANALYSIS 
OF STRESSES ABOUT CUTOUTS IN CIRCULAR 
SEMIMONOCOQUE CYLINDERS WITH FLEXIBLE 
RINGS. Harvey G. McComb, Jr. and Emmet F. 
Low, Jr. July 19&5. 98p. diagrs., 30 tabs. (NACA 
TN 3460) 

COMPARISON BETWEEN THEORETICAL AND EX- 
PERIMENTAL STRESSES IN CIRCULAR SEMI- 
MONOCOQUE CYLINDERS WITH RECTANGULAR 
CUTOUTS. Harvey G. McComb, Jr., and Emmet F. 
Low, Jr. October 1955. 20p. diagrs. 
(NACA TN 3544) 

ON PANEL FLUTTER AND DIVERGENCE OF INFI- 
NITELY LONG UNSTIFFENED AND RING- 
STIFFENED THIN-WALLED CIRCULAR CYLINDERS 
Robert W. Leonard and John M. Hedgepeth. April 
1956. 52p. diagrs. (NACA TN 3638) 



168 



(4) AIRCRAFT LOADS AND CONSTRUCTION 



(4. 3. 5. 2) 
BOXES 

EXPERIMENTAL ANALYSIS OF MULTICELL 
WINGS BY MEANS OF PLASTIC MODELS. George 
W. Zender. June 1955. 6p. diagrs. (NACA 
RM L55E10b) 

INFLUENCE OF SHEAR DEFORMATION ON THE 
CROSS SECTION ON TORSIONAL FREQUENCIES 
OF BOX BEAMS. Edwin T. Kruszewski and William 
W. Davenport. October 1955. 23p. diagrs. (NACA 
TN 3464) 

EXPERIMENTAL INVESTIGATION OF THE VIBRA- 
TIONS OF A BUILT-UP RECTANGULAR BOX 
BEAM. Eldon E. Kordes and Edwin T. Kruszewski. 
February 1956. 28p. diagrs., photos., tabs. 
(NACA TN 3618) 

THE ACCURACY OF THE SUBSTITUTE-STRINGER 
APPROACH FOR DETERMINING THE BENDING 
FREQUENCIES OF MULTISTRINGER BOX BEAMS. 
William W. Davenport. April 1956. 28p. diagrs., 
tab. (NACA TN 3636) 

A METHOD FOR DEFLECTION ANALYSIS OF THIN 
LOU-ASPECT -RATIO WINGS. Manuel Stein and 
J. Lyell Sanders, Jr. June 1956. 65p. diagrs. 
(NACA TN 3640) 

(4.3.6) 
CONNECTIONS 

(4. 3.6. 2) 
RIVETED 

CREEP AND CREEP-RUPTURE CHARACTERISTICS 
OF SOME RIVETED AND SPOT -WELDED LAP 
JOINTS OF AIRCRAFT MATERIALS. Leonard 
Mordfin, National Bureau of Standards. June 1955. 
53p. diagrs., photos., 6 tabs. (NACA TN 3412) 
i 

INVESTIGATION OF THE USE OF A RUBBER ANA- 
LOG IN THE STUDY OF STRESS DISTRIBUTION IN 
RIVETED AND CEMENTED JOINTS. Louis R. 
Demarkles, Massachusetts Institute of Technology. 
November 1955. 97p. diagrs., tabs. 
(NACA TN 3413) 
f 

STATIC SHEAR STRENGTH OF 2117-T4 (A17S-T4) 
ALUMINUM-ALLOY RIVETS AT ELEVATED TEM- 
PERATURES. W. J. Dewalt and K. O. Bogardus, 
Aluminum Company of America. January 1956. 
12p. diagrs., photo., tabs. (NACA RM 55130) 



(4. 3.6. 3) 
WELDED 

CREEP AND CREEP-RUPTURE CHARACTERISTICS 
OF SOME RIVETED AND SPOT -WELDED LAP 
JOINTS OF AIRCRAFT MATERIALS. Leonard 
Mordfin, National Bureau of Standards. June 1955. 
53p. diagrs., photos., 6 tabs. (NACA TN 3412) 

(4. 3.6. 4) 

BONDED 

INVESTIGATION OF THE USE OF A RUBBER ANA- 
LOG IN THE STUDY OF STRESS DISTRIBUTION IN 
RIVETED AND CEMENTED JOINTS. Louis R. 
Demarkles, Massachusetts Institute of Technology. 
November 1955. 97p. diagrs., tabs. 
(NACA TN 3413) 



(4.3.7) 
LOADS AND STRESSES 

TEST OF AN AERODYNAMICALLY HEATED 
MULTIWEB WING STRUCTURE (MW-1) IN A FREE 
JET AT MACH NUMBER 2. Richard R. Heldenlels, 
Richard Rosecrans, and George E. Griffith. July 
1953. 37p. diagrs., photos. (NACA RM L53E27) 

CALIBRATION OF STRAIN-GAGE INSTALLATIONS 
IN AIRCRAFT STRUCTURES FOR THE MEASURE- 
MENT OF FLIGHT LOADS. T. H. Skopinski, 
William S. Aiken, Jr. and Wilber B. Huston. 1954. 
ii, 29p. diagrs., 10 tabs. (NACA Rept. 1178. 
Formerly TN 2993; RM L52G31) 

TABLES OF COEFFICIENTS FOR THE ANALYSIS 
OF STRESSES ABOUT CUTOUTS IN CIRCULAR 
SEMIMONOCOQUE CYLINDERS WITH FLEXIBLE 
RINGS. Harvey G. McComb, Jr. and Emmet F. 
Low, Jr. July 1955. 98p. diagrs., 30 tabs. (NACA 
TN 3460) 

COMPARISON BETWEEN THEORETICAL AND EX- 
PERIMENTAL STRESSES IN CIRCULAR SEMI- 
MONOCOQUE CYLINDERS WITH RECTANGULAR 
CUTOUTS. Harvey G. McComb, Jr., and Emmet F. 
Low, Jr. October 1955. 20p. diagrs. 
(NACA TN 3544) 

SOME EFFECTS OF JOINT CONDUCTIVITY ON THE 

TEMPERATURES AND THERMAL STRESSES IN 
AERODYNAMICALLY HEATED SKIN-STIFFENER 
COMBINATIONS. George E. Griffith and 
Georgene H. Miitonberger. June 1956. 62p. diagrs. 
(NACA TN3699) 



(4.3.7. 1) 
TENSION 

ANALYSIS OF STRESSES IN THE PLASTIC RANGE 
AROUND A CIRCULAR HOLE IN A PLATE SUB- 
JECTED TO UNIAXIAL TENSION. Bernard 
Budiansky and Robert J. Vidensek. October 1955. 
39p. diagrs., tabs. (NACA TN 3542) 



(4. 3.7. 2) 
COMPRESSION 

INVESTIGATION OF THE USE OF A RUBBER ANA- 
LOG IN THE STUDY OF STRESS DISTRIBUTION IN 
RrVETED AND CEMENTED JOINTS. Louis R. 
Demarkles, Massachusetts Institute of Technology. 
November 1955. 97p. diagrs., tabs. 
(NACA TN 3413) 

CHARTS RELATING THE COMPRESSIVE BUCKLING 
STRESS OF LONGITUDINALLY SUPPORTED 
PLATES TO THE EFFECTIVE DEFLECTIONAL AND 
ROTATIONAL STIFFNESS OF THE SUPPORTS. 
Roger A. Anderson and Joseph W. Semonian. 1954. 
ii, 19p. diagrs., tabs. (NACA Rept. 1202. Super- 
sedes TN 2987) 

\ UNIVERSAL COLUMN FORMULA FOR LOAD AT 
WHICH YIELDING STARTS. L. H. Donnell and V. C. 
fsien, Illinois Institute of Technology. October 
'955. 48p. diagrs., photos., tab. (NACA TN 3415) 

CORRELATION OF CRIPPLING STRENGTH OF 
PLATE STRUCTURES WITH MATERIAL PROPER- 
TIES. Roger A. Anderson and Melvin S. Anderson. 
''anuary 1956. 50p. diagrs., tabs. 

NACA TN 3600) 



169 



(4) AIRCRAFT LOADS AND CONSTRUCTION 



ON THE BUCKLING OF BARS AND PLATES IN THE 
PLASTIC RANGE. PART II. (Over het 
knikvraagstuk in het plastische gebied bij staven en 
platen. (Deel)). J. P. Benthem. March 1956. 
79p. diagrs. , tabs. (NACA TM 1392. Trans, of 
Nationaal Luchtvaartlaboratorium, Amsterdam, 
Rapport S. 423, Jan. 1954) 



A THEORY FOR THE ELASTIC DEFLECTIONS OF 
PLATES INTEGRALLY STIFFENED ON ONE SIDE. 
Robert F. Crawford. April 1956, 21p. diagrs, 
(NACA TN 3646) 



CORRELATION OF CREEP -BUCKLING TESTS WITH 
THEORY. Sharad A. Patel, Joseph Kempner, 
Burton Erickson, and Abol H. Mobassery, Poly- 
technic Institute of Brooklyn. May 1956. 39p. 
diagrs., photos., tabs. (NACA RM 56C20) 

(4. 3.7. 3) 

BENDING 

CHARTS RELATING THE COMPRESSIVE BUCKLING 
STRESS OF LONGITUDINALLY SUPPORTED 
PLATES TO THE EFFECTIVE DEFLECTIONAL AND 
ROTATIONAL STIFFNESS OF THE SUPPORTS. 
Roger A. Anderson and Joseph W. Semonian. 1954. 
ll t 19p. diagrs., tabs. (NACA Rept. 1202. Super- 
sedes TN 2987) 

STRESSES AND DEFLECTIONS OF A SWEPT BI- 
PLANE WING. George W. Zender and John E. 
Duberg. August 1954. 41p. diagrs., photo., tabs. 
(NACA RM L54E03a) 

EXPERIMENTAL ANALYSIS OF MULTICELL 
WINGS BY MEANS OF PLASTIC MODELS. George 
W. Zender. June 1955. 6p. diagrs. (NACA 
RM L55E10b) 

ANALYSIS OF THE ULTIMATE STRENGTH AND 
OPTIMUM PROPORTIONS OF MULTIWEB WING 
STRUCTURES. B. Walter Rosen. March 1956. 
34p. diagrs., tabs. (NACA TN 3633) 

A METHOD FOR DEFLECTION ANALYSIS OF THIN 
LOW-ASPECT-RATIO WINGS. Manuel Stein and 
J. Lyell Sanders, Jr. June 1956. 65p. diagrs. 
(NACA TN 3640) 



(4. 3.7.4) 
TORSION 



STRESSES AND DEFLECTIONS OF A SWEPT BI- 
PLANE WING. George W. Zender and John E. 
Duberg. August 1954. 41p. diagrs., photo., tabs. 
(NACA RM L54E03a) 

EXPERIMENTAL ANALYSIS OF MULTICELL 
WINGS BY MEANS OF PLASTIC MODELS. George 
W. Zender. June 1955. 6p. diagrs. (NACA 
RM L55E10b) 

SHEARING EFFECTIVENESS OF INTEGRAL 
STIFFENING. Robert F. Crawford and Charles 
Libove. June 1955. 37p. diagrs., photo., tab. 
(NACA TN 3443) 

A METHOD FOR DEFLECTION ANALYSIS OF THIN 
LOW-ASPECT-RATIO WINGS. Manuel Stein and 
J. Lyell Sanders, Jr. June 1956. 65p. diagrs. 
(NACA TN 3640) 



(4. 3.7. 5) 
SHEAR 

CREEP AND CREEP-RUPTURE CHARACTERISTICS 
OF SOME RIVETED AND SPOT -WELDED LAP 
JOINTS OF AIRCRAFT MATERIALS. Leonard 
Mordfin, National Bureau of Standards. June 1955. 
53p. diagrs., photos., 6 tabs. (NACA TN 3412) 

SHEARING EFFECTIVENESS OF INTEGRAL 
STIFFENING. Robert F. Crawford and Charles 
Libove. June 1955. 37p. diagrs., photo., tab. 
(NACA TN 3443) 

INVESTIGATION OF THE USE OF A RUBBER ANA- 
LOG IN THE STUDY OF STRESS DISTRIBUTION IN 
RIVETED AND CEMENTED JOINTS. Louis R. 
Demarkles, Massachusetts Institute of Technology. 
November 1955. 97p. diagrs., tabs. 
(NACA TN 3413) 



(4. 3.7.6) 

CONCENTRATED 

CREEP AND CREEP-RUPTURE CHARACTERISTICS 
OF SOME RIVETED AND SPOT -WELDED LAP 
JOINTS OF AIRCRAFT MATERIALS. Leonard 
Mordfin, National Bureau of Standards. June 1955. 
53p. diagrs., photos., 6 tabs. (NACA TN 3412) 

ANALYSIS OF STRESSES IN THE PLASTIC RANGE 
AROUND A CIRCULAR HOLE IN A PLATE SUB- 
JECTED TO UNIAXIAL TENSION. Bernard 
Budiansky and Robert J. Vidensek. October 1955. 
39p. diagrs., tabs. (NACA TN 3542) 

STRUCTURAL RESPONSE TO DISCRETE AND 
CONTINUOUS GUSTS OF AN AIRPLANE HAVING 
WING-BENDING FLEXIBILITY AND A CORRELA- 
TION OF CALCULATED AND FLIGHT RESULTS. 
John C. Houbolt and Eldon E. Kordes. 1954. ii, 
22p. diagrs., 4 tabs. (NACA Rept. 1181. Formerly 
TN 3006) 



(4.3.7.7) 

DYNAMIC 

MEASUREMENTS OF NORMAL-FORCE- 
COEFFICIENT FLUCTUATION ON FOUR 9- 
PERCENT-THICK AIRFOILS HAVING DIFFERENT 
LOCATIONS OF MAXIMUM THICKNESS. Milton D. 
Humphreys. April 1954. 21p. diagrs., photos. 
(NACA RM L54B22) 

MEASUREMENT AND ANALYSIS OF WING AND 
TAIL BUFFETING LOADS ON A FIGHTER AIR- 
PLANE. Wilber B. Huston and T. H. Skopinski. 
1955. i, 27p. diagrs., photo., tabs. (NACA Rept. 
1219. Supersedes TN 3080) 

SIMPLIFIED PROCEDURES AND CHARTS FOR THE 
RAPID ESTIMATION OF BENDING FREQUENCIES 
OF ROTATING BEAMS. Robert T. Yntema. June 
1955. ii, 90p. diagrs., 6 tabs. (NACA TN 3459. 
Supersedes and extends RM L54G02) 

A STUDY OF THE RESPONSE OF PANELS TO 
RANDOM ACOUSTIC EXCITATION. Robert W. Hess, 
Leslie W. Lassiter and Harvey H. Hubbard. July 
1955. 9p. diagrs. (NACA RM L55E13c) 



170 



(4) AIRCRAFT LOADS AND CONSTRUCTION 



GUST-TUNNEL INVESTIGATION OF THE EFFECT 
OF A SHARP-EDGE GUST ON THE FLAPWISE 
BLADE BENDING MOMENTS OF A MODEL HELI- 
COPTER ROTOR. Domrnic J Maglieri and Thomas 
D. Reisert. August 1955. 24 p diagrs., photos. 
(NACA TN 3470> 



A REEVALUATION OF GUST-LOAD STATISTICS 
FOR APPLICATIONS IN SPECTRAL CALCULA- 
TIONS. Harry Press and May T. Meadows. 
August 1955. 19p. diagrs. (NACA TN 3540) 



INVESTIGATION OF THE VIBRATIONS OF A HOL- 
LOW THIN-WALLED RECTANGULAR BEAM. 
Eldon E. Kordes and Edwin T. Kruszewsld. October 
1955. 24p. diagrs., photos., 2 tabs. (NACA 
TN 3463) 

INFLUENCE OF SHEAR DEFORMATION ON THE 
CROSS SECTION ON TORSIONAL FREQUENCIES 
OF BOX BEAMS. Edwin T. Kruszewski and William 
W. Davenport. October 1955. 23p. diagrs. (NACA 
TN 3464) 

METHOD AND TABLES FOR DETERMINING THE 
TIME RESPONSE TO A UNIT IMPULSE FROM 
FREQUENCY-RESPONSE DATA AND FOR DETER- 
MINING THE FOURIER TRANSFORM OF A FUNC- 
TION OF TIME. Carl R. Huss and James J. 
Donegan. January 1956. 38p. diagrs., tabs. 
(NACA TN 3598) 

EXPERIMENTAL INVESTIGATION OF THE VIBRA- 
TIONS OF A BUILT-UP RECTANGULAR BOX 
BEAM. Eldon E. Kordes and Edwin T. Kruszewski. 
February 1956. 28p. diagrs., photos., tabs. 
(NACA TN 3618) 



THE ACCURACY OF THE SUBSTITUTE-STRINGER 
APPROACH FOR DETERMINING THE BENDING 
FREQUENCIES OF MULTISTRINGER BOX BEAMS. 
William W. Davenport. April 1956. 28p. diagrs., 
tab. (NACA TN 3636) 



INFLUENCE OF LARGE AMPLITUDES ON FLEX- 
URAL MOTIONS OF ELASTIC PLATES. George 

Herrmann, Columbia University. May 1956. 45p. 
diagrs. (NACA TN 3578) 



(4. 3.7.7. 1) 
Repeated 



AXIAL-LOAD FATIGUE PROPERTIES OF 24S-T 
AND 75S-T ALUMINUM ALLOY AS DETERMINED 
IN SEVERAL LABORATORIES. H. J. Grover and 
W. S. Hyler, Battelle Memorial Institute, PaulKuhn 
and Charles B. Landers, Langley Aeronautical 
Laboratory and F. M. Howell, Aluminum Company 
of America. 1954. ii, 25p. diagrs., photos., 
7 tabs. (NACA Rept. 1190. Formerly TN 2928) 

ON SPECTRAL ANALYSIS OF RUNWAY ROUGHNESS 
AND LOADS DEVELOPED DURING TAXIING. John 
C. Houbolt, James H. Walls and Robert F. Smiley. 
July 1955. 9p. diagrs. (NACA TN 3484) 

INTERIM REPORT ON FATIGUE CHARACTERISTICS 
OF A TYPICAL METAL WING. J. L. Kepert and 
A. O. Payne. March 1956. 80p. diagrs., photos., 
tabs. (NACA TM 1397. Originally issued as Report 
ARL/SM. 207, Aeronautical Research Laboratories, 
Australia) 

RESULTS OF AXIAL-LOAD FATIGUE TESTS ON 
ELECTRO-POLISHED 2024-T3 AND 7075-T6 
ALUMINUM-ALLOY -SHEET SPECIMENS WITH 
CENTRAL HOLES. Charles B. Landers and 
Herbert F. Hardrath. March 1956. 47p. diagrs., 
tabs. (NACA TN 3631) 



(4.3.7.7.2) 
Transient 

EFFECT OF INTERACTION ON LANDING-GEAR 
BEHAVIOR AND DYNAMIC LOADS IN A FLEXIBLE 
AIRPLANE STRUCTURE. Francis E. Cook and 
Benjamin Milwitzky. August 1955. 75p. diagrs., 
2 tabs. (NACA TN 3467) 



(4.3.8) 
WEIGHT ANALYSIS 



ANALYSIS OF THE ULTIMATE STRENGTH AND 
OPTIMUM PROPORTIONS OF MULTIWEB WING 
STRUCTURES. B. Walter Rosen. March 1956. 
34p. diagrs., tabs. (NACA TN 3633) 



(5) 
MATERIALS 



(5) 



171 



(5) MATERIALS 



(5) 
MATERIALS 



PRELIMINARY INVESTIGATION IN J33 TURBOJET 
ENGINE OF SEVERAL ROOT DESIGNS FOR 
CERAMAL TURBINE BLADES. George C. Deutsch, 
Andre J. Meyer, Jr. and William C. Morgan. 
January 1953. 24p. diagrs. , photos. , 2 tabs. 
(NACA RM E52K13) 



172 



(5) MATERIALS 



(5.1) 
Types 



WIRE CLOTH AS POROUS MATERIAL FOR 
TRANSPIRATION-COOLED WALLS. E. R. G. 

Eckert, Martin R. Kinsler, and Reeves P. Cochran. 
November 1951. 38p. diagrs., photos., tab. (NACA 
RM E51H23) 



EXPERIMENTAL INVESTIGATION OF AIR-FLOW 
UNIFORMITY AND PRESSURE LEVEL ON WIRE 
CLOTH FOR TRANSPIRATION-COOLING APPLI- 
CATIONS. Patrick L. Donoughe and Roy A. 
McKinnon. January 1956. 28p. diagrs., photos., 
tab. (NACA TN 3652. Supersedes RM E52E16) 



(5.1.1) 
ALUMINUM 



INVESTIGATION OF EFFECTS OF ADDITIVES ON 
STORAGE PROPERTIES OF FUMING NITRIC ACIDS. 
Charles E. Feller and Gerald Morrell. December 
1952. 25p. photos., diagrs., tabs. 
(NACA RM E52J16) 



AXIAL-LOAD FATIGUE PROPERTIES OF 24S-T 
AND 75S-T ALUMINUM ALLOY AS DETERMINED 
IN SEVERAL LABORATORIES. H. J. Grove r and 
W. S. Hyler, Battelle Memorial Institute, PaulKuhn 
and Charles B. Landers, Langley Aeronautical 
Laboratory and F. M. Howell, Aluminum Company 
of America. 1954. ii, 25p. diagrs., photos., 
7 tabs. (NACA Rept. 1190. Formerly TN 2928) 

TENSILE PROPERTIES OF SOME SHEET MATERI- 
ALS UNDER RAPID-HEATING CONDITIONS. 
George J. Heimerl and John E. Inge. June 1955. 
lOp. diagrs. (NACA RM L55E12b) 

TENSILE PROPERTIES OF 7075 -T6 AND 2024 -T3 
ALUMINUM-ALLOY SHEET HEATED AT UNIFORM 
TEMPERATURE RATES UNDER CONSTANT LOAD. 
George J. Heimerl and John E. Inge. July 1955. 
46p. diagrs., photos., 4 tabs. fNACATN3462) 



CUMULATIVE FATIGUE DAMAGE OF AXIALLY 
LOADED ALCLAD 75S-T6 AND ALCLAD 24S-T3 
ALUMINUM-ALLOY SHEET. Ira Smith, Darnley M. 
Howard, and Frank C. Smith, National Bureau of 
Standards. September 1955. 49p. diagrs., photos., 
5 tabs. (NACA TN 3293) 

METALLOGRAPHY OF ALUMINUM AND ITS 
ALLOYS. USE OF ELECTROLYTIC POLISHING. 
(Metallographie de Taluminium et de ses alliages. 
Emploi dupolissage electrolytique). P. A. Jacquet. 
November 1955. ii, 80p. diagrs., photos., tabs. 
(NACA TM 1384. Trans, from Office National 
d'Etudes et de Recherches Aeronautiques, Pub.51, 
1952) 



GRAIN -BOUNDARY BEHAVIOR IN CREEP OF 
ALUMINUM BICRYSTALS. F. N. Rhines, W. E. 
Bond, and M. A. Kissel, Carnegie Institute of 
Technology. December 1955. 56p. diagrs., photos., 
tabs. (NACA TN 3556) 



RESULTS OF AXIAL-LOAD FATIGUE TESTS ON 
ELECTRO-POLISHED 2024-T3 AND 7075-T6 
ALUMINUM-ALLOY -SHEET SPECIMENS WITH 
CENTRAL HOLES. Charles B. Landers and 
Herbert F. Hardrath. March 1956. 47p. diagrs., 
tabs. (NACA TN 3631) 

ANALYSIS OF THE ULTIMATE STRENGTH AND 
OPTIMUM PROPORTIONS OF MULTIWEB WING 
STRUCTURES. B. Walter Rosen. March 1956. 
34p. diagrs., tabs. (NACA TN 3633) 

INFLUENCE OF ALLOYING UPON GRAIN- 
BOUNDARY CREEP. F. N. Rhines, W. E. Bond and 
M. A. Kissel, Carnegie Institute of Technology. 
April 1956. 16p. diagrs., tab. (NACA TN 3678) 



INVESTIGATION OF PLASTIC BEHAVIOR OF 
BINARY ALUMINUM ALLOYS BY INTERNAL- 
FRICTION METHODS. R. E. Maringer, L. L. 
Marsh, and G. K. Manning, Battelle Memorial 
Institute. June 1956. 44p. diagrs., tabs. 
(NACA TN 3681) 

FATIGUE CRACK PROPAGATION IN SEVERELY 
NOTCHED BARS. W. S. Hyler, E. D. Abraham, 
and H. J. Grover, Battelle Memorial Institute. June 
1956. 31p. diagrs., photos., tabs. (NACA TN 3685) 



(5.1.3) 
STEELS 



INVESTIGATION OF EFFECTS OF ADDITIVES ON 
STORAGE PROPERTIES OF FUMING NITRIC ACIDS. 
Charles E. Feiler and Gerald Morrell. December 
1952. 25p. photos., diagrs., tabs. 
(NACA RM E52J16) 



DYNAMIC CORROSION IN AN IRON -STAIN LESS 
STEEL TOROID BY SODIUM AT 900° F. Robert A. 
Lad. January 15, 1954. 9p. diagrs., tabs. 
(NACA RM E54A27) 



(5.1.4) 
HEAT-RESISTING ALLOYS 

DESIGN FACTORS FOR 4- BY 8-INCH RAM-JET 
COMBUSTOR. Donald W, Male and Adolph J. 
Cervenka. August 11, 1949. 47p. diagrs., photos. 
(NACA RM E9F09) 

INFILTRATION OF TITANIUM CARBIDE WITH 
SEVERAL METALS. Raymonds. Gurnick and 
Anthony L. Cooper. July 1952. 21p. diagrs., 
photos. (NACA RM E52E27) 

INVESTIGATION OF THE Ni 3 Al PHASE OF NICKEL- 
ALUMINUM ALLOYS. Edward M. Grala. April 
1956. 24p. diagrs., photos., tabs. (NACA TN 3660) 



173 



(5) MATERIALS 



(5.1.5) 
CERAMICS 



INFILTRATION OF TITANIUM CARBIDE WITH 
SEVERAL METALS. Raymond S. Gurnick and 
Anthony L. Cooper. July 1952. 21p. diagrs., 
photos. (NACA RM E52E27) 



THE NICKEL DIP: A RADIOISOTOPE STUDY OF 
METALLIC DEPOSITS IN PROCELAIN ENAMELING. 
Joseph C. Richmond, Harry B. Kirkpatrick, and 
William N. Harrison, National Bureau of Standards. 
February 1956. 26p. diagrs., photos., tabs. 
(NACA TN 3577) 



INFLUENCE OF COPPER IONS ON ADHERENCE 
OF VITREOUS COATINGS TO STAINLESS STEEL. 
D. G. Moore and A. G. Eubanks, National Bureau 
of Standards. February 1956. 14p. diagrs., 
photos,, tabs. (NACA TN 3679) 



(5.1.6) 
PLASTICS 



EXPERIMENTAL ANALYSIS OF MULTICELL 
WINGS BY MEANS OF PLASTIC MODELS. George 
W. Zender. June 1955. 6p. diagrs. (NACA 
RM L55E10b) 



INFLUENCE OF TEMPERATURE ON CREEP, 
STRESS-RUPTURE, AND STATIC PROPERTIES OF 
MELAMINE -RESIN AND SILICONE -RESIN GLASS- 
FABRIC LAMINATES. William N. Findley, Harlan 
W. Peithman, and Will J. Worley, University of 
Illinois. January 1956. 71p. diagrs., photos., 
tabs. (NACA TN 3414) 



(5.1.8) 
ADHESIVES 



METAL-BONDING ADHESIVES FOR HIGH- 
TEMPERATURE SERVICE. John M. Black and R. F. 
Blomquist, Forest Products Laboratory. July 1955. 
22p. tab. (NACA RM 55F08) 



(5.1.9) 
PROTECTIVE COATINGS 



EXPERIMENTAL INVESTIGATION OF AIR-COOLED 
TURBINE BLADES IN TURBOJET ENGINE. 
XHI - ENDURANCE EVALUATION OF SEVERAL 
PROTECTIVE COATINGS APPLIED TO TURBINE 
BLADES OF NONSTRATEGIC STEELS. Edward R. 
Bartoo and John L. Clure. July 1953. 40p. photos., 
diagrs., tabs. (NACA RM E53E18) 

THE NICKEL DIP: A RADIOISOTOPE STUDY OF 
METALLIC DEPOSITS IN PROCELAIN ENAMELING. 
Joseph C. Richmond, Harry B. Kirkpatrick, and 
William N. Harrison, National Bureau of Standards. 
February 1956. 26p. diagrs., photos., tabs. 
(NACA TN 3577) 

INFLUENCE OF COPPER IONS ON ADHERENCE 
OF VITREOUS COATINGS TO STAINLESS STEEL. 
D. G. Moore and A. G. Eubanks, National Bureau 
of Standards. February 1956. 14p. diagrs., 
photos., tabs. (NACA TN 3679) 



(5.1.12) 
CERAMALS 



INFILTRATION OF TITANIUM CARBIDE WITH 
SEVERAL METALS. Raymonds. Gurnick and 
Anthony L. Cooper. July 1952. 21p. diagrs.. 

photos. (NACA RM E52E27) 

PRELIMINARY INVESTIGATION IN J33 TURBOJET 
ENGINE OF SEVERAL ROOT DESIGNS FOR 
CERAMAL TURBINE BLADES. George C. Deutsch, 
Andre J. Meyer, Jr. and William C. Morgan. 
January 1953. 24p. diagrs. , photos. , 2 tabs. 
(NACA RM E52K13) 

COMPARATIVE TENSILE STRENGTHS AT 1200° F 
OF VARIOUS ROOT DESIGNS FOR CERMET TUR- 
BINE BLADES. Andre J. Meyer, Jr., Albert 
Kaufman, and Howard F. Calvert. June 1953. 23p. 
diagrs., photos., tabs. (NACA RM E53C25) 



PRELIMINARY INVESTIGATION OF SEVERAL ROOT 
DESIGNS FOR CERMET TURBINE BLADES IN 
TURBOJET ENGINE. H - ROOT DESIGN ALTERA- 
TIONS. A. J. Meyer, Jr., G. C. Deutsch and W. C. 
Morgan. October 1953. 34p. photos., diagrs., tab. 
(NACARM E53G02) 



PRELIMINARY INVESTIGATION OF SEVERAL 
ROOT DESIGNS FOR CERMET TURBINE BLADES 
IN TURBOJET ENGINE. Ill - CURVED-ROOT 
DESIGN Benjamin Pinkel, George C. Deutsch, 
and William C. Morgan. December 1955. 17p. 
diagr., photos., tabs. (NACA RM E55J04) 



174 



(5). MATERIALS 



(5.2) 
Properties 



ON THE PERMEABILITY OF POROUS MATERIALS. 
E. Carson Yates, Jr. January 1956. 31p. diagrs. 
(NACA TN 3596) 

PERFORATED SHEETS AS A POROUS MATERIAL 
FOR DISTRIBUTED SUCTION AND INJECTION. 
Robert E. Dannenberg, Bruno J. Gambucci, and 
James A. Weiberg. April 1956. 27p. diagrs., 
photos. (NACA TN 3669) 



(5.2.1) 
TENSILE 



TENSILE PROPERTIES OF SOME SHEET MATERI- 
ALS UNDER RAPID-HEATING CONDITIONS. 

George J. Heimerl and John E. Inge. June 1955. 
lOp. diagrs. (NACA RM L55E12b) 

METAL-BONDING ADHESIVES FOR HIGH- 
TEMPERATURE SERVICE. John M. Black and R. F. 
Blomquist, Forest Products Laboratory. July 1955. 
22p. tab. (NACA RM 55F08) 

TENSILE PROPERTIES OF 7075-T6 AND 2024-T3 
ALUMINUM-ALLOY SHEET HEATED AT UNIFORM 
TEMPERATURE RATES UNDER CONSTANT LOAD. 
George J. Heimerl and John E. Inge. July 1955. 
46p. diagrs,, photos., 4 tabs. (NACA TN 3462) 

GRAIN-BOUNDARY BEHAVIOR IN CREEP OF 
ALUMINUM BICRYSTALS. F. N. Rhines, W. E. 
Bond, and M. A. Kissel, Carnegie Institute of 
Technology. December 1955. 56p. diagrs., photos., 
tabs. (NACA TN 3556) 

INFLUENCE OF TEMPERATURE ON CREEP, 
STRESS-RUPTURE, AND STATIC PROPERTIES OF 
MELAMTNE-RESIN AND SILICONE-RESIN GLASS- 
FABRIC LAMINATES. William N. Findley, Harlan 
W. Pelthman, and Will J. Worley, University of 
Illinois. January 1956. 71p. diagrs., photos., 
tabs. (NACA TN 3414) 

INVESTIGATION OF THE Ni 3 Al PHASE OF NICKEL- 
ALUMINUM ALLOYS. Edward M. Grala. April 
1956. 24p. diagrs., photos., tabs. (NACA TN 3660) 

INFLUENCE OF ALLOYING UPON GRATN- 
BOUNDARY CREEP. F. N. Rhines, W. E. Bond and 
M. A. Kissel, Carnegie Institute of Technology. 
April 1956. 16p. diagrs., tab. <NACA TN 3678) 



(5.2.2) 
COMPRESSIVE 



INFLUENCE OF TEMPERATURE ON CREEP, 
STRESS-RUPTURE, AND STATIC PROPERTIES OF 

MELAMTNE-RESIN AND SILICONE-RESIN GLASS- 
FABRIC LAMINATES. William N. Findley, Harlan 
W. Peithman, and Will J. Worley, University of 
Illinois. January 1956. 71p. diagrs., photos., 
tabs. (NACA TN 3414) 



CORRELATION OF CRIPPLING STRENGTH OF 
PLATE STRUCTURES WITH MATERIAL PROPER- 
TIES. Roger A. Anderson and Melvin S. Anderson. 
January 1956. 50p. diagrs., tabs. 
(NACA TN 3600) 



(5.2.3) 
CREEP 



EXPERIMENTAL ANALYSIS OF MULTICELL 
WINGS BY MEANS OF PLASTIC MODELS. George 
W. Zender. June 1955. 6p. diagrs. (NACA 
RM L55E10b) 

EFFECT OF SOME SELECTED HEAT TREATMENTS 
ON THE OPERATING LIFE OF CAST HS-21 TUR- 
BINE BLADES. Francis J. Clauss, Floyd B. 
Garrett and John W. vVeeton. July 1955. 39p. 
diagrs., photos. (NACA TN 3512) 

THEORY OF DYNAMIC CREEP. (K teorii 
dinamicheskoi polzuchesti). A. A. Predvoditelev 
and B. A. Smirnov. September 1955. 12p. diagr. 
(NACA TM 1330. Trans, from Moscow Universitet, 
Vestnik, v. 8, no. 8, 1953, p. 79-86) 

INFLUENCE OF TEMPERATURE ON CREEP, 
STRESS-RUPTURE, AND STATIC PROPERTIES OF 
MELAMTNE-RESIN AND SILICONE-RESIN GLASS- 
FABRIC LAMINATES. William N. Findley, Harlan 
W. Peithman, and Will J. Worley, University of 
Illinois. January 1956. 71p. diagrs., photos., 
tabs. (NACA TN 3414) 

INVESTIGATION OF THE COMPRESSIVE 
STRENGTH AND CREEP LIFETIME OF 2024-T3 
ALUMINUM-ALLOY PLATES AT ELEVATED TEM- 
PERATURES. Eldon E. Mathauser and William D. 
Deveikis. January 1956. 40p. diagrs., photos., 
tabs. (NACA TN 3552. Supersedes RM L55Ellb) 



INVESTIGATION OF THE Ni 3 Al PHASE OF NICKEL - 
ALUMINUM ALLOYS. Edward M. Grala. April 
1956. 24p. diagrs., photos., tabs. (NACA TN 3660) 

INFLUENCE OF ALLOYING UPON GRAIN- 
BOUNDARY CREEP. F. N. Rhines, W. E. Bond and 
M. A. Kissel, Carnegie Institute of Technology. 
April 1956. 16p. diagrs., tab. (NACA TN 3678) 

CORRELATION OF CREEP-BUCKLING TESTS WITH 
THEORY. SharadA. Patel, Joseph Kempner, 
Burton Erickson, and Abol H. Mobassery, Poly- 
technic Institute of Brooklyn. May 1956. 39p. 
diagrs., photos., tabs. (NACA RM 56C20) 



INVESTIGATION OF THE COMPRESSIVE STRENGTH 
AND CREEP LIFETIME OF 2024-T ALUMINUM- 
ALLOY SKIN-STRINGER PANELS AT ELEVATED 
TEMPERATURES. Eldon E. Mathauser and 
William D. Deveikis. May 1956. 29p. diagrs., 
photos., tabs. (NACA TN 3647) 



175 



(5) MATERIALS 



(5.2.4) 
STRESS-RUPTURE 



PRELIMINARY INVESTIGATION OF SEVERAL ROOT 
DESIGNS FOR CERMET TURBINE BLADES IN 
TURBOJET ENGINE. II - ROOT DESIGN ALTERA- 
TIONS, A. J. Meyer, Jr., G. C. Deutsch and W. C. 
Morgan. October 1953. 34p. photos. , diagrs. , tab. 
(NACA RM E53G02) 



EFFECT OF SOME SELECTED HEAT TREATMENTS 
ON THE OPERATING LIFE OF CAST HS-21 TUR- 
BINE BLADES. Francis J. Clauss, Floyd B. 
Garrett and John \V. vVeeton. July 1955. 39p. 
diagrs., photos. (NACA TN 3512) 

PRELIMINARY INVESTIGATION OF SEVERAL 
ROOT DESIGNS FOR CERMET TURBINE BLADES 
IN TURBOJET ENGINE. Ill - CURVED-ROOT 
DESIGN. Benjamin Pinkel, George C. Deutsch, 
and William C. Morgan. December 1955. 17p. 
diagr., photos., tabs. (NACA RM E55J04) 

INFLUENCE OF TEMPERATURE ON CREEP, 
STRESS-RUPTURE, AND STATIC PROPERTIES OF 
MELAMINE-RESIN AND SILICONE-RESIN GLASS- 
FABRIC LAMINATES. William N. Findiey, Harlan 
W. Peithman, and Will J. Worley, University of 
Illinois. January 1956. 71p. diagrs., photos., 
tabs. (NACA TN 3414) 

INVESTIGATION OF THE Ni 3 Al PHASE OF NICKEL - 
ALUMINUM ALLOYS. Edward M. Grala. April 
1956. 24p. diagrs., photos., tabs. (NACA TN 3660) 

(5.2.5) 
FATIGUE 

AXIAL-LOAD FATIGUE PROPERTIES OF 24S-T 
AND 75S-T ALUMINUM ALLOY AS DETERMINED 
IN SEVERAL LABORATORIES. H. J. Grover and 
W. S. Hyler, Battelle Memorial Institute, PaulKuhn 
and Charles B. Landers, Langley Aeronautical 
Laboratory and F. M. Howell, Aluminum Company 
of America. 1954. ii, 25p. diagrs., photos., 
7 tabs. (NACA Rept. 1190. Formerly TN 2928) 

CUMULATIVE FATIGUE DAMAGE OF AXIALLY 
LOADED ALCLAD 75S-T6 AND ALCLAD 24S-T3 
ALUMINUM-ALLOY SHEET. Ira Smith, Darnley M. 
Howard, and Frank C. Smith, National Bureau of 
Standards. September 1955. 49p. diagrs., photos., 
5 tabs. (NACA TN 3293) 



FAILURE OF MATERIALS UNDER COMBINED RE- 
PEATED STRESSES WITH SUPERIMPOSED STATIC 
STRESSES. George Sines, University of California 
at Los Angeles. November 1955. 69p. diagrs., 
photos., tabs. (NACA TN 3495) 



INTERIM REPORT ON FATIGUE CHARACTERISTICS 
OF A TYPICAL METAL WING. J. L. Kepert and 
A. O. Payne. March 1956. 80p. diagrs., photos., 
tabs. (NACA TM 1397. Originally issued as Report 
ARL/SM. 207, Aeronautical Research Laboratories, 
Australia) 



RESULTS OF AXIAL-LOAD FATIGUE TESTS ON 
ELECTRO-POLISHED 2024-T3 AND 7075-T6 
ALUMINUM-ALLOY-SHEET SPECIMENS WITH 
CENTRAL HOLES. Charles B. Landers and 
Herbert F. Hardrath. March 1956. 47p. diagrs., 
tabs. (NACA TN 3631) 



ELEVATED-TEMPERATURE FATIGUE PROPER- 
TIES OF TWO TITANIUM ALLOYS. William K. 
Rey, University of Alabama. April 24, 1956. 28p. 
diagrs., photo., tabs. (NACA RM 56B07) 

FATIGUE CRACK PROPAGATION IN SEVERELY 
NOTCHED BARS. W. S. Hyler, E. D. Abraham, 
and H. J. Grover, Battelle Memorial Institute. June 
1956. ,3lp. diagrs., photos., tabs. (NACA TN 3685) 



(5.2.6) 
SHEAR 



SHEARING EFFECTIVENESS OF INTEGRAL 
STIFFENING. Robert F. Crawford and Charles 
Libove. June 1955. 37p. diagrs., photo., tab. 
(NACA TN 3443) 



METAL-BONDING ADHESIVES FOR HIGH- 
TEMPERATURE SERVICE. John M. Black and R. F. 
Blomquist, Forest Products Laboratory. July 1955. 
22p. tab. (NACA RM 55F08) 



STATIC SHEAR STRENGTH OF 2117-T4 (A17S-T4) 
ALUMINUM-ALLOY RIVETS AT ELEVATED TEM- 
PERATURES. W. J. Dewalt and K. O. Bogardus, 
Aluminum Company of America. January 1956. 
12p. diagrs., photo., tabs. (NACA RM 55130) 



(5.2.7) 
FLEXURAL 



EXPERIMENTAL ANALYSIS OF MULTICELL 
WINGS BY MEANS OF PLASTIC MODELS. George 
W. Zender. June 1955. 6p. diagrs. (NACA 
RM L55E10b) 



(5.2.8) 
CORROSION RESISTANCE 

INVESTIGATION OF EFFECTS OF ADDITIVES ON 
STORAGE PROPERTIES OF FUMING NITRIC ACIDS. 
Charles E. Feller and Gerald Morrell. December 
1952. 25p. photos., diagrs., tabs. 
(NACA RM E52J16) 



DYNAMIC CORROSION IN AN IRON -STAIN LESS 
STEEL TOROID BY SODIUM AT 900° F. Robert A. 
Lad. January 15, 1954. 9p. diagrs., tabs. 
(NACARM E54A27) 



INVESTIGATION OF EFFECT OF FLUORIDE ON 
CORROSION OF 2S-0 ALUMINUM AND 347 STAIN- 
LESS STEEL IN FUMING NITRIC ACID AT 170° F. 
Charles E. Feller and Gerald Morrell. February 
1954. 22p. diagrs., photos., tabs. 
(NACARM E53L17b) 



THE NICKEL DIP: A RADIOISOTOPE STUDY OF 
METALLIC DEPOSITS IN PROCELAIN ENAMELING. 
Joseph C. Richmond, Harry B. Kirkpatrick, and 
William N. Harrison, National Bureau of Standards. 
February 1956. 26p. diagrs., photos., tabs. 
(NACA TN 3577) 



176 



(5) MATERIALS 



INVESTIGATION OF THE Ni 3 Al PHASE OF NICKEL- 
ALUMINUM ALLOYS. Edward M. Grala. April 
1956. 24p. diagrs., photos., tabs. (NACA TN 3660) 



(5.2.9) 
STRUCTURE 



EFFECT OF SOME SELECTED HEAT TREATMENTS 
ON THE OPERATING LIFE OF CAST HS-21 TUR- 
BINE BLADES. Francis J. Clauss, FLoyd B. 
Garrett and John W. Weeton. July 1955. 39o. 
diagrs., photos. (NACA TN 3512) 



METALLOGRAPHY OF ALUMINUM AND ITS 
ALLOYS. USE OF ELECTROLYTIC POLISHING. 
(Metallographie de l'aluminium et de ses alliages. 
Emploi dupolissage electrolytique). P. A. Jacquet. 
November 1955. ii, 80p. diagrs., photos., tabs. 
(NACA TM 1384. Trans, from Office National 
d'itudes et de Recherches Aeronautlques, Pub.51, 
1952) 



GRAIN-BOUNDARY BEHAVIOR IN CREEP OF 
ALUMINUM BICRYSTALS. F. N. Rhines, W. E. 
Bond, and M. A. Kissel, Carnegie Institute of 
Technology. December 1955. 56p. diagrs., photos., 
tabs. (NACA TN 3556) 



CORRELATION OF SUPERSONIC CONVECTIVE 
HEAT-TRANSFER COEFFICIENTS FROM MEAS- 
UREMENTS OF THE SKIN TEMPERATURE OF A 
PARABOLIC BODY OF REVOLUTION (NACA RM-10). 
Leo T. Chauvin and Carlo*: A. deMoraes. March 
1956. 38p. diapr-., photo., tabs. (NACA TN 3623. 
Supersedes RM L51A18) 



INFLUENCE OF ALLOYING UPON GRAIN- 
BOUNDARY CREEP. F. N. Rhines, W. E. Bond and 
M. A. Kissel, Carnegie Institute of Technology. 
April 1956. 16p. diagrs., tab. (NACA TN 3678) 



(5.2/IO) 
EFFECTS OF NUCLEAR RADIATION 



DYNAMIC CORROSION IN AN IRON -STAIN LESS 
STEEL TOROID BY SODIUM AT 900° F. Robert A. 
Lad. January 15, 1954. 9p. diagrs., tabs. 
(NACA RM E54A27) 



(5.2.11) 
THERMAL 

TENSILE PROPERTIES OF SOME SHEET MATERI- 
ALS UNDER RAPID-HEATING CONDITIONS. 
George J. Heimerl and John E. Inge. June 1955. 
lOp. diagrs. (NACA RM L55E12b) 

METAL-BONDING ADHESIVES FOR HIGH- 
TEMPERATURE SERVICE. John M. Black and R. F. 
Blomquist, Forest Products Laboratory. July 1955. 
22p. tab. (NACA RM 55F08) 

TENSILE PROPERTIES OF 7075 -T6 AND 2024 -T3 
ALUMINUM-ALLOY SHEET HEATED AT UNIFORM 
TEMPERATURE RATES UNDER CONSTANT LOAD. 
George J. Heimerl and John E. Inge. July 1955. 
46p. diagrs., photos., 4 tabs. (NACA TN 3462) 



DEVELOPMENT OF EQUDPMENT AND OF EXPERI- 
MENTAL TECHNIQUES FOR COLUMN CREEP 
TESTS. Sharad A. Patel, Martin Bloom, Burton 
Erickson, Alexander Chwick and N(icholas) J(ohn) 
Hoff, Polytechnic Institute of Brooklyn. September 
1955. 20p. diagrs. , photos. , tab. (NACA TN 3493) 



RESPONSE OF HOMOGENEOUS AND TWO- 
MATERIAL LAMINATED CYLINDERS TO SINUSOI- 
DAL ENVIRONMENTAL TEMPERATURE CHANGE, 
WITH APPLICATIONS TO HOT-WIRE ANEMOM- 
ETRY AND THERMOCOUPLE PYROMETRY. 
Herman H. Lowell and Norman (A.) Patton. 
September 1955. ii, 143p. diagrs. , tabs. (NACA 
TN 3514) 

STATIC SHEAR STRENGTH OF 2117-T4 (A17S-T4) 
ALUMINUM-ALLOY RIVETS AT ELEVATED TEM- 
PERATURES. W. J. Dewalt and K. O. Bogardus, 
Aluminum Company of America. January 1956. 
12p, diagrs., photo., tabs. (NACA RM 55130) 



(5.2.13) 
PLASTICITY 



GRAIN-BOUNDARY BEHAVIOR IN CREEP OF 
ALUMINUM BICRYSTALS. F. N. Rhines, W. E. 
Bond, and M. A. Kissel, Carnegie Institute of 
Technology. December 1955. 56p. diagrs., photos., 
tabs. (NACA TN 3556) 



INFLUENCE OF ALLOYING UPON GRAIN- 
BOUNDARY CREEP. F. N. Rhines, W. E. Bond and 
M. A. Kissel, Carnegie Institute of Technology. 
April 1956. 16p. diagrs., tab. (NACA TN 3678) 



177 



(5) MATERIALS 



(5.3) 
Operating Stresses and Conditions 



PRELIMINARY INVESTIGATION IN J33 TURBOJET 
ENGINE OF SEVERAL ROOT DESIGNS FOR 
CERAMAL TURBINE BLADES. George C. Deutsch, 
Andre J. Meyer, Jr. and William C. Morgan. 
January 1953. 24p. diagrs. , photos. , 2 tabs. 
(NACA RM E52K13) 

COMPARATIVE TENSILE STRENGTHS AT 1200° F 
OF VARIOUS ROOT DESIGNS FOR CERMET TUR- 
BINE BLADES. Andre J. Meyer, Jr., Albert 
Kaufman, and Howard F. Calvert. June 1953. 23p. 
diagrs., photos., tabs. (NACA RM E53C25) 



A STUDY OF THE RESPONSE OF PANELS TO 
RANDOM ACOUSTIC EXCITATION. Robert W. Hess, 
Leslie W. Lassiter and Harvey H. Hubbard. July 
1955. 9p. diagrs. (NACA RM L55E 13c) 



(5.3.2) 
PROPULSION SYSTEM 

PRELIMINARY INVESTIGATION IN J33 TURBOJET 
ENGINE OF SEVERAL ROOT DESIGNS FOR 
CERAMAL TURBINE BLADES. George C. Deutsch, 
Andre J. Meyer, Jr. and William C. Morgan. 
January 1953. 24p. diagrs., photos., 2 tabs. 
(NACA RM E52K13) 



PRELIMINARY INVESTIGATION OF SEVERAL ROOT 
DESIGNS FOR CERMET TURBINE BLADES IN 
TURBOJET ENGINE. H - ROOT DESIGN ALTERA- 
TIONS. A. J. Meyer, Jr., G, C. Deutsch and W. C. 
Morgan. October 1953. 34p. photos. , diagrs. , tab. 
(NACA RM E53G02) 



EXPERIMENTAL INVESTIGATION OF AIR-COOLED 
TURBINE BLADES IN TURBOJET ENGINE. XIV - 
ENDURANCE EVALUATION OF SHELL-SUPPORTED 
TURBINE ROTOR BLADES MADE OF TIMKEN 
17-22A(S) STEEL. Francis S. Stepka, H. Robert 
Bear, and John L. Clure. September 1954. 29p. 
diagrs., photos., tabs. (NACA RM E54F23a) 



PRELIMINARY INVESTIGATION OF SEVERAL 
ROOT DESIGNS FOR CERMET TURBINE BLADES 
IN TURBOJET ENGINE. Ill - CURVED-ROOT 
DESIGN. Benjamin Pinkel, George C. Deutsch, 
and William C. Morgan. December 1955. 17p. 
diagr., photos., tabs. (NACA RM E55J04) 



THE DESIGN OF A MINIATURE SOLID- 
PROPELLANT ROCKET. Robert H. Heitkotter. 
March 1956. 13p. diagrs., photo., tab. 
(NACA TN 3620) 



(6) 
METEOROLOGY 



(6) 



179 



(6) METEOROLOGY 



(6) 
METEOROLOGY 



IMPINGEMENT OF CLOUD DROPLETS ON A CYL- 
INDER AND PROCEDURE FOR MEASURING LIQUID- 
WATER CONTENT AND DROPLET SIZES IN SUPER- 
COOLED CLOUDS BY ROTATING MULTICYLINDER 
METHOD. R. J. Brun, W. Lewis, P. J. Perkins 
and J. S. Serafini. Appendix E: ALTERNATE 
METHOD OF REDUCING ROTATING MULTICYL- 
INDER DATA. Paul T. Hacker. 1955. iv, 43p. 
diagrs., photos., tabs. (NACA Rept. 1215. Super- 
sedes TN 2903; TN 2904; RM E53D23) 



IMPINGEMENT OF WATER DROPLETS ON A 
SPHERE. Robert G. Dorsch, Paul G. Saper, and 
Charles F. Kadow. November 1955. 29p. diagrs., 
tab. (NACA TN 3587) 



180 



(6) METEOROLOGY 



(6.1) 
Atmosphere 



IMPINGEMENT OF CLOUD DROPLETS ON A CYL- 
INDER AND PROCEDURE FOR MEASURING LIQUID- 
WATER CONTENT AND DROPLET SIZES IN SUPER- 
COOLED CLOUDS BY ROTATING MULTICYLINDER 
METHOD. R. J. Brun, W. Lewis, P. J. Perkins 
and J. S. Seraf ini. Appendix E: ALTERNATE 
METHOD OF REDUCING ROTATING MULTICYL- 
INDER DATA. Paul T. Hacker. 1955. iv, 43p. 
diagrs., photos., tabs. (NACA Rept. 1215. Super- 
sedes TN 2903; TN 2904; RM E53D23) 



(6.1.1) 
STANDARD ATMOSPHERE 



STANDARD ATMOSPHERE— TABLES AND DATA 
FOR ALTITUDES TO 65,800 FEET. International 
Civil Aviation Organization, Montreal, Canada and 
Langley Aeronautical Laboratory, Langley Field, 
Va. 1955, v, 114p. tabs. (NACA Rept. 1235. 
Supersedes TN 3182; Rept. 218) 



(6.1.2) 
GUSTS 



THE VARIATION OF ATMOSPHERIC TURBULENCE 
WITH ALTITUDE AND ITS EFFECT ON AIRPLANE 
GUST LOADS. Robert L. McDougal, Thomas L. 
Coleman and Philip L. Smith. November 1953. 16p. 
diagrs., 2 tabs. (NACA RM L53G15a) 



SOME DESIGN CONSIDERATIONS PERTINENT TO 
THE ROUGH -AIR BEHAVIOR OF AIRPLANES AT 
LOW ALTITUDE. Philip Donely and Clarence L. 
Gillis. November 1953. 21p. diagrs., tabs. 
(NACA RM L53J01b) 



STRUCTURAL RESPONSE TO DISCRETE AND 
CONTINUOUS GUSTS OF AN AIRPLANE HAVING 
WING-BENDING FLEXIBILITY AND A CORRELA- 
TION OF CALCULATED AND FLIGHT RESULTS. 
JohnC. Houbolt and Eldon E. Kordes. 1954. ii, 
22p. diagrs., 4 tabs. (NACA Rept. 1181. Formerly 
TN 3006) 



A REVISED GUST-LOAD FORMULA AND A RE- 
EVALUATION OF V-G DATA TAKEN ON CIVIL 
TRANSPORT AIRPLANES FROM 1933 TO 1950. 
Kermit G. Pratt and Walter G. Walker. 1954. ii, 
9p. diagrs., tabs. (NACA Rept. 1206. Supersedes 
TN 2964; TN 3041) 



A REEVALUATION OF GUST-LOAD STATISTICS 
FOR APPLICATIONS IN SPECTRAL CALCULA- 
TIONS. Harry Press and May T. Meadows. 
August 1955. 19p. diagrs. (NACA TN 3540) 



AN ANALYSIS OF ACCELERATION, AIRSPEED, 
AND GUST-VELOCITY DATA FROM A FOUR- 
ENGINE TRANSPORT AIRPLANE IN OPERATIONS 
ON AN EASTERN UNITED STATES ROUTE. 
Thomas L. Coleman and Mary W. Fetner. September 
1955. 20p. diagrs., 3 tabs. (NACA TN 3483) 



AN ANALYSIS OF ACCELERATION, AIRSPEED, 
AND GUST -VELOCITY DATA FROM ONE TYPE OF 
FOUR-ENGINE TRANSPORT AIRPLANE OPERATED 
OVER TWO DOMESTIC ROUTES. Martin R. Copp 
and Thomas L. Coleman. October 1955. 29p. 

diagrs., tabs. (NACA TN 3475) 



SUMMARY OF DERIVED GUST VELOCITIES OB- 
TAINED FROM MEASUREMENTS WITHIN THUN- 
DERSTORMS. H(arold) B. Tolefson. October 
1955. 19p. diagrs., tabs. (NACA TN 3538) 



GUST -LOAD AND AIRSPEED DATA FROM ONE 
TYPE OF TWO-ENGINE AIRPLANE ON SDC CIVIL 
AIRLINE ROUTES FROM 1947 TO 1955. Walter G. 
Walker. February 1956. 25p. diagrs., tabs. 
(NACA TN 3621) 



SUMMARY OF LOCATIONS AND EXTENTS OF TUR- 
BULENT AREAS ENCOUNTERED DURING FLIGHT 
INVESTIGATIONS OF THE JET STREAM FROM 
OCTOBER 1953 TO MAY 1954 AND NOVEMBER 1954 
TO JULY 1955, Mary W. Fetner. April 1956. 
lOp. tab. (NACA RM L55H04a) 



(6. 1. 2. 1) 
STRUCTURE 



MEASUREMENTS OF ATMOSPHERIC TURBULENCE 
OVER A WIDE RANGE OF WAVELENGTH FOR ONE 
METEOROLOGICAL CONDITION. Harold L. Crane 
and Robert G. Chilton. June 1956. 18p. diagrs., 
photo. (NACA TN 3702) 



(6. 1.2.2) 

FREQUENCY 



MEASUREMENTS OF ATMOSPHERIC TURBULENCE 
OVER A WIDE RANGE OF WAVELENGTH FOR ONE 
METEOROLOGICAL CONDITION. Harold L. Crane 
and Robert G. Chilton. June 1956. 18p. diagrs., 
photo. (NACA TN 3702) 



181 



(6) METEOROLOGY 



(6. 1.2.3) 
TURBULENCE 



MEASUREMENTS OF ATMOSPHERIC TURBULENCE 
OVER A WIDE RANGE OF WAVELENGTH FOR ONE 
METEOROLOGICAL CONDITION. Harold L. Crane 
and Robert G. Chilton. June 1956. 18p. diagrs., 
photo. (NACA TN 3702) 



(6. 1.2.4) 

ALLEVIATION 



METEOROLOGICAL PROBLEMS ASSOCIATED 
WITH COMMERCIAL TUBOJET-AIRCRAFT OPER- 
ATION. A working group of the NACA Subcommittee 
on Meteorological Problems. June 1955. 46p. 
(NACA RM 54L29) 



THEORETICAL STUDY OF THE LATERAL FRE- 
QUENCY RESPONSE TO GUSTS OF A FIGHTER AIR- 
PLANE, BOTH WITH CONTROLS FIXED AND WITH 
SEVERAL TYPES OF AUTOPILOTS. James J. 
Adams and Charles W. Mathews, March 1956. 46p. 
diagrs., tabs. (NACA TN 3603) 



ANALYTICAL STUDY OF MODIFICATIONS TO THE 
AUTOPILOT OF A FIGHTER AIRPLANE IN ORDER 
TO REDUCE THE RESPONSE TO SIDE GUSTS. 
Charles W. Mathews and James J. Adams. March 
1956. 35p. diagrs., tabs. (NACA TN 3635) 



ANALYSIS OF A VANE -CONTROLLED GUST- 
ALLEVIATION SYSTEM. Robert W. Boucher and 
Christopher C. Kraft, Jr. April 1956. 45p. 
diagrs., tabs. (NACA TN 3597) 



INITIAL RESULTS OF A FLIGHT INVESTIGATION 
OF A GUST-ALLEVIATION SYSTEM. Christopher 
C. Kraft, Jr. April 1956. 19p. diagrs., photos., 
tabs. (NACA TN 3612) 



AN INVESTIGATION OF FORWARD-LOCATED 
FDCED SPOILERS AND DEFLECTORS AS GUST 
ALLEVIATORS ON AN UNSWEPT-WING MODEL. 
Del win R. Croom, C C. Snuff lebarger, and 
Jarrett K. Huffman. June 1956. 26p. diagrs., 
photo. (NACA TN 3705) 



182 



(6) METEOROLOGY 



(6.2) 
Ice Formation 



IMPINGEMENT OF CLOUD DROPLETS ON A CYL- 
INDER AND PROCEDURE FOR MEASURING LIQUID- 
WATER CONTENT AND DROPLET SIZES IN SUPER- 
COOLED CLOUDS BY ROTATING MULTICYLINDER 
METHOD. R. J. Brun, W. Lewis, P. J. Perkins 
and J. S. Serafini. Appendix E: ALTERNATE 
METHOD OF REDUCING ROTATING MULTICYL- 
INDER DATA. Paul T. Hacker. 1955, iv, 43p. 
diagrs., photos,, tabs. (NACA Rept. 1215. Super- 
sedes TN 2903; TN 2904; RM E53D23) 

METEOROLOGICAL PROBLEMS ASSOCIATED 
WITH COMMERCIAL TUBOJET-AIRCRAFT OPER- 
ATION. A working group of the NACA Subcommittee 
on Meteorological Problems. June 1955. 46p. 
(NACA RM 54L29) 



STATISTICAL SURVEY OF ICING DATA MEASURED 
ON SCHEDULED AIRLINE FLIGHTS OVER THE 
UNITED STATES AND CANADA FROM NOVEMBER 
1951 TO JUNE 1952. Porter J. Perkins. 
September 1955. 44p. diagrs., photos., 2 tabs. 
(NACA RM E55F28a) 



IMPINGEMENT OF WATER DROPLETS ON NACA 
65A004 AIRFOIL AT 0° ANGLE OF ATTACK. 
Rinaldo J. Brun and Dorothea E. Vogt. November 
1955. 28p. diagrs. (NACA TN 3586) 



IMPINGEMENT OF WATER DROPLETS ON A 
SPHERE. Robert G. Dorsch, Paul G. Saper, and 
Charles F. Kadow. November 1955. 29p. diagrs., 

tab. (NACA TN 3587) 



CLOUD-DROPLET INGESTION IN ENGINE INLETS 
WITH INLET VELOCITY RATIOS OF 1.0 AND 0.7. 
Rinaldo J. Brun. January 1956. 52p. diagrs., tao. 
(NACA TN 3593) 



IMPINGEMENT OF WATER DROPLETS ON A REC- 
TANGULAR HALF BODY IN A TWO-DIMENSIONAL 
INCOMPRESSIBLE FLOW FIELD. William Lewis 
and Rinaldo J. Brun. February 1956. 27p. diagrs., 
tabs, (NACA TN 3658) 



(7) 
OPERATING PROBLEMS 



(7) 



183 



(7) OPERATING PROBLEMS 



(7) 
OPERATING PROBLEMS 



FLIGHT DETERMINATION OF THE EFFECTS OF 
RUDDER-PEDAL-FORCE CHARACTERISTICS ON 
THE AIMING ERROR IN AZIMUTH OF A CONVEN- 
TIONAL FIGHTER AIRPLANE. Lee Winograd and 
Rudolph D. Van Dyke, Jr. July 5, 1950. 32p. 
diagrs., photos., tab. (NACA RM A50D06) 

THE VARIATION OF ATMOSPHERIC TURBULENCE 
WITH ALTITUDE AND ITS EFFECT ON AIRPLANE 
GUST LOADS. Robert L. McDougal, Thomas L. 
Coleman and Philip L. Smith. November 1953. 16p. 
diagrs., 2 tabs. (NACA RM L53G15a) 

SOME DESIGN CONSIDERATIONS PERTINENT TO 
THE ROUGH-AIR BEHAVIOR OF AIRPLANES AT 
LOW ALTITUDE. Philip Doneiy and Clarence L. 
Gillis. November 1953. 21p. diagrs., tabs. 
(NACA RM L53J01b) 

A REVISED GUST-LOAD FORMULA AND A RE- 
fcVALUA HON OF V-G DATA TAKEN ON CIVIL 
TRANSPORT AIRPLANES FROM 1933 TO 1950. 
Kermit G. Pratt and Walter G. Walker. 1954. ii, 
9p. diagrs., tabs. (NACA Rept. 1206. Supersedes 
TN 2964; TN 3041) 

SUMMARY EVALUATION OF TOOTHED-NOZZLE 
ATTACHMENTS AS A JET -NOISE -SUPPRESSION 
DEVICE. Warren J. North. July 1955. 19p. 
diagrs., photo. (NACA TN 3516) 

AN ANALYSIS OF ACCELERATION, AIRSPEED, 
AND GUST -VELOCITY DATA FROM A FOUR- 
ENGINE TRANSPORT AIRPLANE IN OPERATIONS 
ON AN EASTERN UNITED STATES ROUTE. 
Thomas L. Coleman and Mary W. Fetner. September 
1955. 20p. diagrs., 3 tabs. (NACA TN 3483) 

AN ANALYSIS OF ACCELERATION, AIRSPEED, 
AND GUST-VELOCITY DATA FROM ONE TYPE OF 
FOUR-ENGINE TRANSPORT AIRPLANE OPERATED 
OVER TWO DOMESTIC ROUTES. Martin R. Copp 
and Thomas L. Coleman. October 1955. 29p. 

diagrs., tabs. (NACA TN 3475) 

SUMMARY OF DERIVED GUST VELOCITIES OB- 
TAINED FROM MEASUREMENTS WITHIN THUN- 
DERSTORMS. H(arold) B. Tolefson. October 
1955. 19p. diagrs., tabs. (NACA TN 3538) 



EFFECT OF EXHAUST -NOZZLE EJECTORS ON 
TURBOJET NOISE GENERATION. Warren J. North 
and Willard D. Coles. October 1955. 26p. diagrs., 
photo. (NACA TN 3573) 

HELICOPTER INSTRUMENT FLIGHT AND PRECI- 
SION MANEUVERS AS AFFECTED BY CHANGES IN 
DAMPING IN ROLL, PITCH, AND YAW. James B. 
Whitten, John P. Reeder, and Aimer D. Crim. 
November 1955. 14p. diagrs., photos. 
(NACA TN 3537) 

EFFECT OF CLIMB TECHNIQUE ON JET- 
TRANSPORT NOISE. Warren J. North. January 
1956. 19p. diagrs. (NACA TN 3582) 

INVESTIGATION OF FAR NOISE FIELD OF JETS 

I - EFFECT OF NOZZLE SHAPE. Edmund E. 
Callaghan and Willard D. Coles. January 1956. 
44p. diagrs., photos. (NACA TN 3590) 

INVESTIGATION OF FAR NOISE FIELD OF JETS. 

II - COMPARISON OF AIR JETS AND JET ENGINES. 
Willard D. Coles and Edmund E. Callaghan. 
January 1956. 19p. diagrs., photos. 

(NACATN 3591) 

GUST -LOAD AND AIRSPEED DATA FROM ONE 
TYPE OF TWO-ENGINE AIRPLANE ON SIX CIVIL 
AIRLINE ROUTES FROM 1947 TO 1955. Walter G. 
Walker. February 1956. 25p. diagrs., tabs. 
(NACA TN 3621) 

SUMMARY OF SCALE-MODEL THRUST -REVERSER 
INVESTIGATION. John H. Povolny, Fred W. 
Steffen, and Jack G. McArdle. February 1956. 
49p. diagrs., photos. (NACA TN 3664) 

PRELIMINARY FLIGHT SURVEY OF AERODY- 
NAMIC NOISE ON AN AIRPLANE WING. Harold R. 
Mull and Joseph S. Algranti. March 1956. 8p. 
diagrs. (NACA RM E55K07) 

INVESTIGATION OF THE EFFECT OF IMPACT 
DAMAGE ON FATIGUE STRENGTH OF JET-ENGINE 
COMPRESSOR ROTOR BLADES. Albert Kaufman 
and Andre J. Meyer, Jr. June 1956. 25p. diagrs., 
photos. (NACA TN 3275) 



184 



(7) OPERATING PROBLEMS 



(7.1) 
Safety 



METEOROLOGICAL PROBLEMS ASSOCIATED 
WITH COMMERCIAL TUBOJET-AIRCRAFT OPER- 
ATION. A working group of the NACA Subcommittee 
on Meteorological Problems. June 1955. 46p. 
(NACA RM 54L29) 



PRELIMINARY DATA ON RAIN DEFLECTION FROM 
AIRCRAFT WINDSHIELDS BY MEANS CF HIGH- 
VELOCITY JET -AIR BLAST. Robert S. Ruggeri. 
July 1955. 17p. diagrs., photos. (NACA 
RM E55E17a) 



FULL-SCALE PERFORMANCE STUDY OF A PRO- 
TOTYPE CRASH- FIRE PROTECTION SYSTEM FOR 
RECIPROCATING-ENGINE-POWERED AIRPLANES. 
Dugald O. Black and Jacob C. Moser. November 
1955. 36p. diagrs., photos. (NACA RM E55B11) 



PERFORMANCE AND OPERATIONAL STUDIES OF 
A FULL-SCALE JET- ENGINE THRUST REVERSER. 
Robert C. Kohl. April 1956. 38p. diagrs., photo. 
(NACA TN 3665) 



(7.1.1) 
PILOT- ESCAPE TECHNIQUES 



AERODYNAMIC MEASUREMENTS MADE DURING 
NAVY INVESTIGATION OF HUMAN TOLERANCE 
TO WIND BLASTS. Donald L. Loving. March 11, 
1947. 34p. diagrs., photos., 2 tabs. (NACA 
RM L7C25) 



185 



(7) OPERATING PROBLEMS 



(7.2) 
Navigation 



METEOROLOGICAL PROBLEMS ASSOCIATED 
WITH COMMERCIAL TUBOJET -AIRCRAFT OPER- 
ATION. A working group of the NACA Subcommittee 
on Meteorological ProbLems. June 1955. 46p. 
(NACA RM 54L29) 



WIND-TUNNEL INVESTIGATION OF A NUMBER OF 
TOTAL-PRESSURE TUBES AT HIGH ANGLES OF 
ATTACK. SUBSONIC, TRANSONIC, AND SUPER- 
SONIC SPEEDS. William Gr^cey. May 1956. 
30p. diagrs., tabs. (NACA TN 3641) 



186 



(7) OPERATING PROBLEMS 



(7.3) 
Ice Prevention and Removal 



IMPINGEMENT OF CLOUD DROPLETS ON A CYL- 
INDER AND PROCEDURE FOR MEASURING LIQUID- 
WATER CONTENT AND DROPLET SIZES IN SUPER- 
COOLED CLOUDS BY ROTATING MULTICYLINDER 
METHOD. R. J. Brun, W. Lewis, P. J. Perkins 
and J. S. Serafini. Appendix E: ALTERNATE 
METHOD OF REDUCING ROTATING MULTICYL- 
INDER DATA. Paul T. Hacker. 1955. iv, 43p. 
diagrs., photos., tabs. (NACA Rept. 1215. Super- 
sedes TN 2903; TN 2904; RM E53D23) 



METEOROLOGICAL PROBLEMS ASSOCIATED 
WITH COMMERCIAL TUBOJET -AIRCRAFT OPER- 
ATION. A working group of the NACA Subcommittee 
on Meteorological Problems. June 1955. 46p, 
(NACA RM 54L29) 



STATISTICAL SURVEY OF ICING DATA MEASURED 
ON SCHEDULED AIRLINE FLIGHTS OVER THE 
UNITED STATES AND CANADA FROM NOVEMBER 
1951 TO JUNE 1952. Porter J. Perkins. 
September 1955. 44p. diagrs., photos., 2 tabs. 
(NACA RM E55F28a) 



IMPINGEMENT OF WATER DROPLETS ON A 
SPHERE. Robert G. Dor sen, Paul G. Saper, and 
Charles F. Kadow. November 1955. 29p. diagrs., 
tab. (NACA TN 3587) 



AN OIL-STREAM PHOTOMICROGRAPHIC AERO- 
SCOPE FOR OBTAINING CLOUD LIQUID-WATER 
CONTENT AND DROPLET SIZE DISTRIBUTIONS 
IN FLIGHT. Paul T. Hacker. January 1956. 36p. 
diagrs., photos., tabs. (NACA TN 3592) 



IMPINGEMENT OF WATER DROPLETS ON A REC- 
TANGULAR HALF BODY IN A TWO-DIMENSIONAL 
INCOMPRESSIBLE FLOW FIELD. William Lewis 
andRinaldoJ. Brun. February 1956. 27p. diagrs., 
tabs. (NACA TN 3658) 



(7.3.1) 
ENGINE INDUCTION SYSTEMS 



CLOUD -DROPLET INGESTION IN ENGINE INLETS 
WITH INLET VELOCITY RATIOS OF 1.0 AND 0.7. 
Rinaldo J. Brun. January 1956. 52p. diagrs., tao. 
(NACA TN 3593) 



(7.3.2) 
PROPELLERS 



IMPINGEMENT OF WATER DROPLETS ON NACA 
65A004 AIRFOIL AT 0° ANGLE OF ATTACK. 
Rinaldo J. Brun and Dorothea E. Vogt. November 
1955. 28p. diagrs. (NACA TN 3586) 



(7.3.3) 
WINGS AND TAILS 



IMPINGEMENT OF WATER DROPLETS ON NACA 
65A004 AIRFOIL AT 0° ANGLE OF ATTACK. 
Rinaldo J, Brun and Dorothea E. Vogt. November 
1955. 28p. diagrs. (NACA TN 3586) 



EFFECT OF PNEUMATIC DE-ICERS AND ICE 
FORMATIONS ON AERODYNAMIC CHARACTERIS- 
TICS OF AN AIRFOIL. Dean T. Bowden. February 
1956. 59p. diagrs., photos. (NACA TN 3564) 



(7.3.4) 
WINDSHIELDS 



PRELIMINARY DATA ON RAIN DEFLECTION FROM 
AIRCRAFT WINDSHIELDS BY MEANS OF HIGH- 
VELOCITY JET-AIR BLAST. Robert S. Ruggeri. 
July 1955. 17p. diagrs., photos. (NACA 
RM E55E17a) 



(7.3.5) 
MISCELLANEOUS ACCESSORIES 



CLOUD-DROPLET INGESTION IN ENGINE INLETS 
WITH INLET VELOCITY RATIOS OF 1.0 AND 0.7. 
Rinaldo J. Brun. January 1956. 52p. diagrs., tao. 
(NACA TN 3593) 



(7.3.6) 
PROPULSION SYSTEMS 



CLOUD-DROPLET INGESTION IN ENGINE INLETS 
WITH INLET VELOCITY RATIOS OF 1.0 AND 0.7. 
Rinaldo J. Brun. January 1956. 52p. diagrs., tao. 
(NACA TN 3593) 



187 



(7) OPERATING PROBLEMS 



(7.4) 
Noise 



THEORETICAL AND EXPERIMENTAL INVESTIGA- 
TION OF MUFFLERS WITH COMMENTS ON 
ENGINE-EXHAUST MUFFLER DESIGN. Don D. 
Davis, Jr., George M. Stokes, Dewey Moore, and 
George L. Stevens, Jr. 1954. iv, 47p. dlagrs., 
photos., tabs. (NACA Rept. 1192. Supersedes 
TN 2893; TN 2943) 



A THEORETICAL STUDY OF THE EFFECT OF 
FORWARD SPEED ON THE FREE-SPACE SOUND- 
PRESSURE FIELD AROUND PROPELLERS. I. E. 
Garrick and Charles E. Watkins. 1954. ii, 16p. 
diagrs., tab. (NACA Rept. 1198. Supersedes 
TN 3018) 



SHOCK-TURBULENCE INTERACTION AND THE 
GENERATION OF NOISE. H. S. Ribner, 1955. 
iii, 19p. diagrs., tab. (NACA Rept. 1233. Super- 
sedes TN 3255) 



METEOROLOGICAL PROBLEMS ASSOCIATED 
WITH COMMERCIAL TUBOJET-AIRCRAFT OPER- 
ATION. A working group of the NACA Subcommittee 
on Meteorological Problems. June 1955. 46p. 
(NACA RM 54L29) 



ACOUSTICAL TREATMENT FOR THE NACA 8- BY 
6-FOOT SUPERSONIC PROPULSION WIND TUNNEL. 
Leo L. Beranek, Samuel Labate and Uno Ingard, 
Bolt Beranek and Newman, Inc. June 1955. 86p. 
diagrs., photo., 7 tabs. (NACA TN 3378) 



A STUDY OF THE RESPONSE OF PANELS TO 
RANDOM ACOUSTIC EXCITATION. Robert W. Hess, 
Leslie W. Lassiter and Harvey H. Hubbard. July 
1955. 9p. diagrs. (NACA RM L55E13c) 



NOISE SURVEY OF A 10-FOOT FOUR-BLADE 
TURBINE -DRIVEN PROPELLER UNDER STATIC 
CONDITIONS. Max C. Kurbjun. July 1955. 25p. 
diagrs., photo. (NACA TN 3422) 



SUMMARY EVALUATION OF TOOTHED -NOZZLE 
ATTACHMENTS AS A JET -NOISE -SUPPRESSION 
DEVICE. Warren J. North. July 1955. 19p. 
diagrs., photo. (NACA TN 3516) 



ACOUSTIC RADIATION FROM TWO-DIMENSIONAL 
RECTANGULAR CUTOUTS IN AERODYNAMIC 
SURFACES. K. Krishnamurty, California Institute 
of Technology. August 1955. 33p. diagrs., photos. 
(NACA TN 3487) 



SOME MEASUREMENTS OF FLOW IN A RECTAN- 
GULAR CUTOUT. Anatoi Roshko, California 
Institute of Technology, August 1955. 21p. diagrs. 
(NACA TN 3488) 



INTENSITY, SCALE, AND SPECTRA OF TURBU- 
LENCE IN MIXING REGION OF FREE SUBSONIC 
JET. James C. Laurence, September 1955. 58p. 
diagrs., photo., tab. (NACA TN 3561) 



SOUND PROPAGATION INTO THE SHADOW ZONE 
IN A TEMPERATURE-STRATIFIED ATMOSPHERE 
ABOVE A PLANE BOUNDARY. David C. Pridmore- 
Brown and Uno Ingard, Massachusetts Institute of 
Technology. October 1955. 57p. diagrs., photo. 
(NACA TN 3494) 



STUDY OF SCREECHING COMBUSTION IN A 
6-INCH SIMULATED AFTERBURNER. Perry L. 
Blackshear, Warren D. Rayle, and Leonard K. 
Tower. October 1955. 58p. diagrs., photos., tab. 
(NACA TN 3567) 



EFFECT OF EXHAUST-NOZZLE EJECTORS ON 
TURBOJET NOISE GENERATION. Warren J. North 
and Willard D. Coles. October 1955. 26p. diagrs., 
photo. (NACA TN 3573) 



A THEORETICAL ANALYSIS OF THE FIELD OF A 
RANDOM NOISE SOURCE ABOVE AN INFINITE 
PLANE. Peter A. Franken, Massachusetts Insti- 
tute of Technology. November 1955. 20p. diagrs. 
(NACA TN 3557) 



INSTRUMENTATION FOR MEASUREMENT OF 
FREE-SPACE SOUND PRESSURE IN THE IMMEDI- 
ATE VICINITY OF A PROPELLER IN FLIGHT. 
William D. Mace, Francis J. Haney, and Edmund 
A. Brummer. January 1956. 16p. diagrs., 
photo. (NACA TN 3534) 



EFFECT OF CLIMB TECHNIQUE ON JET- 
TRANSPORT NOISE. Warren J. North. January 
1956. 19p. diagrs. (NACA TN 3582) 



INVESTIGATION OF FAR NOISE FIELD OF JETS. 
I - EFFECT OF NOZZLE SHAPE. Edmund E. 
Callaghan and Willard D. Coles. January 1956. 
44p. diagrs., photos. (NACA TN 3590) 



INVESTIGATION OF FAR NOISE FIELD OF JETS. 
II - COMPARISON OF AIR JETS AND JET ENGINES. 

Willard D. Coles and Edmund E. Callaghan. 
January 1956. 19p. diagrs., photos. 
(NACA TN 3591) 



PRELIMINARY FLIGHT SURVEY OF AERODY- 
NAMIC NOISE ON AN AIRPLANE WING. Harold R. 
Mull and Joseph S. Algranti, March 1956. 8p, 
diagrs. (NACA RM E55K07) 



188 



(7) OPERATING PROBLEMS 



(7.7) 
Piloting Techniques 



FLIGHT DETERMINATION OF THE EFFECTS OF 
RUDDER-PEDAL-FORCE CHARACTERISTICS ON 
THE AIMING ERROR IN AZIMUTH OF A CONVEN- 
TIONAL FIGHTER AIRPLANE. Lee Winograd and 
Rudolph D. Van Dyke, Jr. July 5, 1950. 32p. 
diagrs., photos., tab. (NACA RM A50D06) 



EFFECT OF FORMATION POSITION ON LOAD 
FACTORS OBTAINED ON F2H AIRPLANES. Carl R. 
Huss and Harold A. Hamer. December 1951. 15p. 
diagrs., 3 tabs. (NACA RM L51I05) 



REVIEW AND INVESTIGATION OF UNSATISFAC- 
TORY CONTROL CHARACTERISTICS INVOLVING 
INSTABILITY OF PILOT-AIRPLANE COMBINATION 
AND METHODS FOR PREDICTING THESE DIFFI- 
CULTIES FROM GROUND TESTS. William H. 
Phillips, B. Porter Brown, and James T. Matthews, 
Jr. August 1953. 57p. diagrs., photos. 
(NACA RML53F17a) 



OPTIMUM FLIGHT PATHS OF TURBOJET AIR- 
CRAFT. (Traiettorie Ottime Di Volo Degli Aero- 
plani Azionati Da Turboreattori). Angelo Miele. 
September 1955. 47p. diagrs. , tabs. (NACA TM 
1389. Trans, from L'Aerotecnica, v. 32, no. 4, 
1952, p. 206-219) 



GENERAL SOLUTIONS OF OPTIMUM PROBLEMS 
IN NONSTATIONARY FLIGHT. (Soluzioni Generali 
di Problemi di Ottimo in Volo Non-Stazionario). 
Angelo Miele. October 1955. 25p. diagrs., tab. 
(NACA TM 1388. Trans, from L'Aerotecnica, v.32, 
no.3, 1952, p.135-142) 



PILOT'S LOSS OF ORIENTATION IN INVERTED 
SPINS. Stanley H. Scher. October 1955. lOp. 
diagrs., photos. (NACA TN 3531) 



THE PROBLEM OF REDUCING THE SPEED OF A 
JET TRANSPORT IN FLIGHT. Don D. Davis, Jr. 
December 1955. 22p. diagrs. (NACA TN 3613) 



189 



(7) OPERATING PROBLEMS 



(7.8) 
Physiological 



AERODYNAMIC MEASUREMENTS MADE DURING 
NAVY INVESTIGATION OF HUMAN TOLERANCE 
TO WIND BLASTS. Donald L. Loving. March 11, 
1947. 34p. diagrs., photos., 2 tabs. (NACA 
RM L7C25) 



190 



(7) OPERATING PROBLEMS 



(7.9) 
Fire Hazards 



FLAME PROPAGATION LIMITS OF PROPANE AND 
n-PENTANE IN OXIDES OF NITROGEN. Riley O. 
Miller. August 1955. 29p. diagrs., 3 tabs. (NACA 
TN3520) 



FULL-SCALE PERFORMANCE STUDY OF A PRO- 
TOTYPE CRASH-FIRE PROTECTION SYSTEM FOR 
RECIPROCATING-ENGINE-POWERED AIRPLANES. 
Dugald O. Black and Jacob C, Moser. November 
1955. 36p. diagrs., photos. (NACA RM E55B11) 



191 



(7) OPERATING PROBLEMS 



(7.10) 
General 



LIFT AND DRAG CHARACTERISTICS OF THE 
BELL X-5 RESEARCH AIRPLANE AT 59° SWEEP- 
BACK FOR MACH NUMBERS FROM 0,60 TO 1,03. 
Donald R. Bellman. February 1953. 37p. diagrs., 
photos., tab. (NACA RM L53A09c) 



CONSIDERATIONS IN THE ADAPTATION OF LOW- 
COST FUELS TO GAS-TURBINE-POWERED COM- 
MERCIAL AIRCRAFT. Henry C. Barnett and 
Richard J. McCafferty. October 1953. 59p. diagrs., 
photo., 2 tabs. (NACA RM E53H05) 



AN ANALYTICAL STUDY OF THE EFFECT OF 
AIRPLANE WAKE ON THE LATERAL DISPERSION 
OF AERIAL SPRAYS. Wilmer H. Reed, in. 1954. 
ii, 16p. diagrs., 3 tabs. (NACA Rept. 1196. 
Formerly TN 3032) 



PRELIMINARY DATA ON RAIN DEFLECTION FROM 
AIRCRAFT WINDSHIELDS BY MEANS OF HIGH- 
VELOCITY JET-AIR BLAST. Roberts. Ruggeri. 
July 1955. 17p. diagrs., photos. (NACA 
RM E55E17a) 



THE PROBLEM OF REDUCING THE SPEED OF A 
JET TRANSPORT IN FLIGHT. Don D. Davis, Jr. 
December 1955. 22p. diagrs. (NACA TN 3613) 



INVESTIGATION OF FAR NOISE FIELD OF JETS 
I - EFFECT OF NOZZLE SHAPE. Edmund E. 
Callaghan and Willard D. Coles. January 1956. 
44p. diagrs., photos. (NACA TN 3590) 



INVESTIGATION OF FAR NOISE FIELD OF JETS. 
II - COMPARISON OF AIR JETS AND JET ENGINES. 
Willard D. Coles and Edmund E. Callaghan. 
January 1956. 19p. diagrs., photos. 
(NACA TN 3591) 



PRELIMINARY FLIGHT SURVEY OF AERODY- 
NAMIC NOISE ON AN AIRPLANE WING. Harold R. 
Mull and Joseph S. Algranti. March 1956. 8p, 
diagrs. (NACA RM E55K07) 

INVESTIGATION OF THE EFFECT OF IMPACT 
DAMAGE ON FATIGUE STRENGTH OF JET-ENGINE 
COMPRESSOR ROTOR BLADES. Albert Kaufman 
and Andre J, Meyer. Jr. June 1956. 25d. diagrs.. 
photos. (NACA TN 3275) 



(8) 
INSTRUMENTS 



(8) 



193 



(8) INSTRUMENTS 



(8) 
INSTRUMENTS 



ROCKET-POWERED FLIGHT TEST OF A ROLL- 
STABILIZED SUPERSONIC MISSILE CONFIGURA- 
TION. Robert A. Gardiner and Jacob Zarovsky. 
January 12, 1950. 32p. diagrs., photos., tab. 
(NACA RM L9K01a) 



FLIGHT INVESTIGATION OF A ROLL-STABILIZED 
MISSILE CONFIGURATION AT VARYING ANGLES 
OF ATTACK AT MACH NUMBERS BETWEEN 0.8 
AND 1.79. Jacob Zarovsky and Robert A. Gardiner. 
March 6, 1951. 38p. diagrs., photos., tab. 
(NACA RM L50H21) 



METEOROLOGICAL PROBLEMS ASSOCIATED 
WITH COMMERCIAL TUBOJET- AIRCRAFT OPER- 
ATION. A working group of the NACA Subcommittee 
on Meteorological Problems. June 1955. 4bp. 
(NACA RM 54L29) 



INTENSITY, SCALE, AND SPECTRA OF TURBU- 
LENCE IN MDCING REGION OF FREE SUBSONIC 
JET. James C. Laurence. September 1955. 58p. 
diagrs., photo., tab. (NACA TN 3561) 



AVERAGING OF PERIODIC PRESSURE PULSA- 
TIONS BY A TOTAL -PRESSURE PROBE. R. C. 
Johnson. October 1955. 30p. diagrs., photo., 
tabs. (NACA TN 3568) 



INSTRUMENTATION FOR MEASUREMENT OF 
FREE-SPACE SOUND PRESSURE IN THE IMMEDI- 
ATE VICINITY OF A PROPELLER IN FLIGHT. 
William D. Mace, Francis J. Haney, and Edmund 
A. Brummer. January 1956. 16p. diagrs., 
photo, (NACA TN 3534) 



194 



(8) INSTRUMENTS 



(8.1) 
Flight 



FLIGHT CALIBRATION OF ANGLE-OF-ATTACK 
AND SIDESLIP DETECTORS ON THE FUSELAGE 
OF A 35° SWEPT -WING FIGHTER AIRPLANE. 
Norman M. McFadden, George A. Rathert, Jr., and 
RichardS. Bray. February 1952. 26p. diagrs., 
photos. (NACA RM A52A04) 

COMPARISON OF MEASURED AND PREDICTED 
INDICATED ANGLES OF ATTACK NEAR THE 
FUSELAGES OF A TRIANGULAR -WING WIND- 
TUNNEL MODEL AND A SWEPT -WING FIGHTER 
AIRPLANE IN FLIGHT. Norman M. McFadden, 
John L. McCloud, III, and Harry A. James. 
March 1953. 13p. diagrs. (NACA RM A53A15) 

AN AIR-FLOW-DIRECTION PICKUP SUITABLE FOR 
TELEMETERING USE ON PILOTLESS AIRCRAFT. 
Wallace L. Ikard. March 1954. 25p. diagrs., 
photos. (NACA RM L53K16) 



WIND-TUNNEL INVESTIGATION OF A SHIELDED 
TOTAL-PRESSURE TUBE AT A MACH NUMBER OF 
1.61. Walter R. Russell and William Gracey. 
March 1954. 9p. diagrs., photo. (NACA 
RM L53L23a) 

RECOVERY AND TIME-RESPONSE CHARACTER- 
ISTICS OF SDC THERMOCOUPLE PROBES IN SUB- 
SONIC AND SUPERSONIC FLOW. Truman M. 
Stickney. July 1955. 25p. diagrs., photos., 2 tabs. 
(NACA TN 3455) 

FLIGHT CALIBRATION OF FOUR AIRSPEED SYS- 
TEMS ON A SWEPT-WING AIRPLANE AT MACH 
NUMBERS UP TO 1.04 BY THE NACA RADAR- 
PHOTOTHEODOLITE METHOD. Jim Rogers 
Thompson, RichardS. Bray, and George E . Cooper. 
November 1955. 41p. diagrs., photos., tab. 
(NACA TN 3526. Supersedes RM A50H24) 



INSTRUMENTATION FOR MEASUREMENT OF 
FREE-SPACE SOUND PRESSURE IN THE IMMEDI- 
ATE VICINITY OF A PROPELLER IN FLIGHT. 
William D. Mace, Francis J. Haney, and Edmund 
A. Brummer. January 1956. 16p. diagrs., 
photo. (NACA TN 3534) 

AN OIL-STREAM PHOTOMICROGRAPHIC AERO- 
SCOPE FOR OBTAINING CLOUD LIQUID-WATER 
CONTENT AND DROPLET SIZE DISTRIBUTIONS 
INFLIGHT. Paul T. Hacker. January 1956. 36p. 
diagrs., photos., tabs. (NACA TN 3592) 

ERROR IN AIRSPEED MEASUREMENT DUE TO 
THE STATIC -PRESSURE FIELD AHEAD OF AN 
AIRPLANE AT TRANSONIC SPEEDS. Thomas C. 
O'Bryan, Edward C. B. Danforth, and J. Ford 
Johnston. February 1956. 13p. diagrs., photos. 
(NACA Rept. 1239. Supersedes RM L9C25; 
RM L50L28; RM L52A17) 



IMPINGEMENT OF WATER DROPLETS ON A REC- 
TANGULAR HALF BODY IN A TWO-DIMENSIONAL 
INCOMPRESSIBLE FLOW FIELD. William Lewis 
andRinaldoJ. Brun. February 1956. 27p. diagrs., 
tabs. (NACA TN 3658) 

WIND-TUNNEL INVESTIGATION OF A NUMBER OF 
TOTAL-PRESSURE TUBES AT HIGH ANGLES OF 
ATTACK. SUBSONIC, TRANSONIC, AND SUPER- 
SONIC SPEEDS. William Gracey. May 1956. 
30p. diagrs., tabs. (NACA TN 3641) 



A SONIC-FLOW ORIFICE PROBE FOR THE IN- 
FLIGHT MEASUREMENT OF TEMPERATURE 
PROFILES OF A JET ENGINE EXHAUST WITH 
AFTERBURNING. C. Dewey Havlll and L. Stewart 
Rolls. May 1956. 18p. diagrs., photos. 
(NACA TN 3714) 



195 



(8) INSTRUMENTS 



(8.2) 
Laboratory 



RECOVERY AND TIME-RESPONSE CHARACTER- 
ISTICS OF SIX THERMOCOUPLE PROBES IN SUB- 
SONIC AND SUPERSONIC FLOW. Truman M. 
Stickney. July 1955. 25p. diagrs., photos., 2 tabs. 
(NACA TN 3455) 

AN AUTOMATIC VISCOMETER FOR NON- 
NEWTONIAN MATERIALS. Ruth N. Weltmann and 
Perry W. Kuhns. August 1955. 34p. diagrs., 
photos., tab. (NACA TN 3510) 



RESPONSE OF HOMOGENEOUS AND TWO- 
MATERIAL LAMINATED CYLINDERS TO SINUSOI- 
DAL ENVIRONMENTAL TEMPERATURE CHANGE, 
WITH APPLICATIONS TO HOT-WIRE ANEMOM- 
ETRY AND THERMOCOUPLE PYROMETRY. 
Herman H. Lowell and Norman (A. ) Patton. 
September 1955. ii, 143p. diagrs. , tabs. (NACA 
TN 3514) 



HEAT LOSS FROM YAWED HOT WIRES AT SUB- 
SONIC MACH NUMBERS. Virgil A. Sandborn and 
James C. Laurence. September 1955. 44p. 
diagrs., photo. (NACA TN 3563) 



STUDY OF SCREECHING COMBUSTION IN A 
6-INCH SIMULATED AFTERBURNER. Perry L. 
Blackshear, Warren D. Rayle, and Leonard K. 
Tower. October 1955. 58p. diagrs., photos., tab. 
(NACA TN 3567) 



AN OIL-STREAM PHOTOMICROGRAPHIC AERO- 
SCOPE FOR OBTAINING CLOUD LIQUID-WATER 
CONTENT AND DROPLET SIZE DISTRIBUTIONS 
IN FLIGHT. Paul T. Hacker. January 1956. 36] 
diagrs., photos., tabs. (NACA TN 3592) 



TIME CORRELATOR FOR PROBLEMS IN AERO- 
DYNAMICS. George Tolmie Skinner, California 
Institute of Technology. June 1956. 32p. diagrs. 
(NACA TN 3682) 



APPLICATION OF SCATTERING THEORY TO THE 
MEASUREMENT OF TURBULENT DENSITY FLUC- 
TUATIONS BY AN OPTICAL METHOD. Howard A. 
Stine and Warren Winovich. June 1956. 21p. diagrs., 
(NACA TN 3719) 



AN EVALUATION OF FOUR EXPERIMENTAL 
METHODS FOR MEASURING MEAN PROPERTIES 
OF A SUPERSONIC TURBULENT BOUNDARY 
LAYER. George J. Nothwang. June 1956. 34p. 
diagrs., photos. (NACA TN 3721) 



196 



(8) INSTRUMENTS 



(8.3) 
Meteorological 



AN OIL-STREAM PHOTOMICROGRAPHIC AERO- 
SCOPE FOR OBTAINING CLOUD LIQUID-WATER 
CONTENT AND DROPLET SIZE DISTRIBUTIONS 
IN FLIGHT. Paul T. Hacker. January 1956. 36p. 
diagrs., photos., tabs. (NACA TN 3592) 



IMPINGEMENT OF WATER DROPLETS ON A REC- 
TANGULAR HALF BODY IN A TWO-DIMENSIONAL 
INCOMPRESSIBLE FLOW FIELD. William Lewis 
and Rinaldo J. Brun. February 1956. 27p. diagrs., 
tabs. (NACA TN 3658) 



(9) 

RESEARCH EQUIPMENT 

AND TECHNIQUES 



(9) 



197 



(9) RESEARCH EQUIPMENT AND TECHNIQUES 



(9) 

RESEARCH EQUIPMENT 

AND TECHNIQUES 



AN NACA TRANSONIC TEST SECTION WITH 
TAPERED SLOTS TESTED AT MACH NUMBERS TO 
1.26. Vernon G. Ward, Charles F. Whitcomb, and 
Merwin D. Pearson. March 30, 1950. 19p. 
diagrs., photos., tab. (NACA RM L50B14) 

PRESSURE DISTRIBUTIONS AT MACH NUMBERS 
FROM 0.6 TO 1.9 MEASURED IN FREE FLIGHT ON 
A PARABOLIC BODY OF REVOLUTION WITH 
SHARPLY CONVERGENT AFTERBODY. William E. 
Stoney, Jr. April 195^. 34p. diagrs., photos. 
(NACA RM L51L03) 

NACA TRANSONIC WIND-TUNNEL TEST SECTIONS 
RayH. Wright and Vernon G. Ward. 1955. ii, 38p. 
diagrs,, photos., tabs. (NACA Rept. 1231. Super- 
sedes RM L8J06) 

ACOUSTICAL TREATMENT FOR THE NACA 8- BY 
6-FOOT SUPERSONIC PROPULSION WIND TUNNEL. 
Leo L. Beranek, Samuel Labate and Uno Ingard, 
Bolt Beranek and Newman, Inc. June 1955. 86p. 
diagrs., photo., 7 tabs. (NACA TN 3378) 



ANALYSIS OF A SPIN AND RECOVERY FROM 
TIME HISTORIES OF ATTITUDES AND VELOCI- 
TIES AS DETERMINED FOR A DYNAMIC MODEL 
OF A CONTEMPORARY FIGHTER AIRPLANE IN 
THE FREE-SPINNING TUNNEL. Stanley H. Scher. 
April 1956. 54p. diagrs., photos., tabs. 
(NACA TN 3611) 



MEASUREMENT OF AERODYNAMIC FORCES FOR 
VARIOUS MEAN ANGLES OF ATTACK ON AN AIR- 
FOIL OSCILLATING IN PITCH AND ON TWO 
FINITE-SPAN WINGS OSCILLATING IN BENDING 
WITH EMPHASIS ON DAMPING IN THE STALL 
A. Gerald Rainey. May 1956. i, 66p. diagrs 
photo. (NACA TN 3643) "' 



TIME CORRELATOR FOR PROBLEMS IN AERO- 
DYNAMICS. George Tolmie Skinner, California 
Institute of Technology. June 1956. 32p. diagrs. 
(NACA TN 3682) 



198 



(9) RESEARCH EQUIPMENT AND TECHNIQUES 



(9.1) 
Equipment 



AN NACA TRANSONIC TEST SECTION WITH 
TAPERED SLOTS TESTED AT MACH NUMBERS TO 
1.26. Vernon G. Ward, Charles F. Whitcomb, and 
Merwin D. Pearson. March 30, 1950. 19p. 
diagrs., photos., tab. (NACA RM L50B14) 



DYNAMIC STABILITY AND CONTROL CHARACTER- 
ISTICS OF A VERTICALLY RISING AIRPLANE 
MODEL IN HOVERING FLIGHT. William R. Bates, 
Powell M. Lovell, Jr., and Charles C. Smith, Jr. 
February 23, 1951. 16p. diagrs., photos., tab. 
(NACA RM L50J16) 



EFFECT OF THE PROXIMITY OF THE GROUND ON 
THE STABILITY AND CONTROL CHARACTERIS- 
TICS OF A VERTICALLY RISING AIRPLANE MODEL 
IN THE HOVERING CONDITION. Charles C. Smith, 
Jr., Powell M. Lovell, Jr., and William R. Bates. 
September 1951. 16p. diagrs., tab. (NACA 
RM L51G05) 



ADDITIONAL STUDIES OF THE STABILITY AND 
CONTROLLABILITY OF AN UNSWEPT-WTNG 
VERTICALLY RISING AIRPLANE MODEL IN 
HOVERING FLIGHT INCLUDING STUDIES OF VAR- 
IOUS TETHERED LANDING TECHNIQUES. 
William R. Bates, Powell M. Lovell, Jr., and 
Charles C. Smith, Jr. November 1951. 25p. 
diagrs., photos., tab. (NACA RM L51I07a) 



WIND-TUNNEL INVESTIGATION OF THE EFFECTS 
OF STEADY ROLLING ON THE AERODYNAMIC 
LOADING CHARACTERISTICS OF A 45° SWEPT- 
BACK WING AT HIGH SUBSONIC SPEEDS. James 
W. Wiggins and Richard E. Kuhn. November 1953. 
22p. diagrs., photos. (NACA RM L53J01a) 



A STUDY OF THE CHARACTERISTICS OF HUMAN- 
PILOT CONTROL RESPONSE TO SIMULATED AIR- 
CRAFT LATERAL MOTIONS. Donald C. Cheatham. 
1954. ii, 14p. diagrs., photos., tab. (NACA 
Rept. 1197. Formerly RM L52C 17) 



DEVELOPMENT OF TURBULENCE-MEASURING 
EQUIPMENT. Leslie S. G. Kovasznay, John 
Hopkins University. 1954. ii, 30p, diagrs., 
photos., tab. (NACA Rept. 1209. Supersedes 
TN 2839) 



AN INVESTIGATION OF A METHOD FOR OBTAIN- 
ING HYDRODYNAMIC DATA AT VERY HIGH 
SPEEDS WITH A FREE WATER JET. Bernard 
Weinflash and John R. McGehee. June 1954. 28p. 
diagrs., photos., tabs. (NACA RM L54D23) 



NACA TRANSONIC WIND-TUNNEL TEST SECTIONS. 
Ray H. Wright and Vernon G. Ward. 1955. ii, 38p. 
diagrs., photos., tabs. (NACA Rept. 1231. Super- 
sedes RM L8J06) 



DOWNWASH SURVEY BEHIND TWO LOW-ASPECT- 
RATIO VARIABLE -INCIDENCE WINGS IN COMBI- 
NATION WITH THREE DIFFERENT SIZE FUSE- 
LAGES AT A MACH NUMBER OF 0.25. Edward J. 
Hopkins and Norman E. Sorensen. March 1955. 54p. 
diagrs., photos., tab. (NACA RM A55A07) 



PRACTICAL CONSIDERATIONS IN SPECIFIC 
APPLICATIONS OF GAS-FLOW INTERFEROMETRY. 
Walton L. Howes and Donald R. Buchele. July 1955. 
ii, 95p. diagrs., photos. (NACA TN 3507) 



MEASUREMENTS OF TURBULENT SKIN FRICTION 
ON A FL^T PLATE AT TRANSONIC SPEEDS. 

Raimo J(aakko) Hakkinen, California Institute of 
Technology. September 1955. 41p. diagrs. , photo, 
tabs. (NACA TN 3486) 



A METHOD FOR OBTAINING STATISTICAL DATA 
ON AIRPLANE VERTICAL VELOCITY AT GROUND 
CONTACT FROM MEASUREMENTS OF CENTER- 
OF -GRAVITY ACCELERATION. Robert C. Dreher. 
February 1956. 21p. diagrs., photo., tabs. 
(NACA TN 3541) 



MEASUREMENTS OF ATMOSPHERIC TURBULENCE 
OVER A WIDE RANGE OF WAVELENGTH FOR ONE 
METEOROLOGICAL CONDITION. Harold L. Crane 
and Robert G. Chilton. June 1956. 18p. diagrs., 
photo. (NACA TN 3702) 



(9.1.1) 
WIND TUNNELS 



AN NACA TRANSONIC TEST SECTION WITH 
TAPERED SLOTS TESTED AT MACH NUMBERS TO 
1.26. Vernon G. Ward, Charles F. Whitcomb, and 
Merwin D. Pearson. March 30, 1950. 19p. 
diagrs., photos., tab. (NACA RM L50B14) 



PRESSURE MEASUREMENTS ON A BODY OF REVO- 
LUTION IN THE LANGLEY 16-FOOT TRANSONIC 
TUNNEL AND A COMPARISON WITH FREE-FALL 
DATA. Joseph M. Hallissy, Jr. March 1952. I9p. 
diagrs. (NACA RM L5lL07a) 



AN EXPERIMENTAL INVESTIGATION OF BOUND- 
ARY INTERFERENCE ON FORCE AND MOMENT 
CHARACTERISTICS OF LIFTING MODELS IN THE 

LANGLEY 16- AND 8-FOOT TRANSONIC TUNNELS. 
Charles F. Whitcomb and Robert S. Osborne. 
February 1953. 31p. photos., diagrs., tab. 
(NACA RM L52L29) 



199 



(9) RESEARCH EQUIPMENT AND TECHNIQUES 



A PRELIMINARY INVESTIGATION OF THE POWER 
REQUIREMENTS OF SLOTTED TEST SECT T ONS. 
John S. Dennard. July 1953. 32p. diagrs. 
(NACARML53F10) 



SLOTTED-BOUNDARY INTERFERENCE EFFECTS 
ON WEDGE AIRFOILS AT LOW SUPERSONIC MACH 
NUMBERS. William J. Nelson and Allen R. Vick. 
July 1953. 27p. diagrs., photos. 
(NACA RM L53F11) 



AN EXPERIMENTAL INVESTIGATION OF THE 
TRANSONIC-FLOW-GENERATION AND SHOCK- 
WAVE-REFLECTION CHARACTERISTICS OF A 
TWO-DIMENSIONAL WIND TUNNEL WITH 17- 
PERCENT-OPEN PERFORATED WALLS. Don D. 
Davis, Jr., Thomas B. Sellers, and George M. Stokes. 
April 1954. 40p. diagrs., photos. 
(NACA RM L54B15a) 



A FREE-FLIGHT WIND TUNNEL FOR AERODY- 
NAMIC TESTING AT HYPERSONIC SPEEDS. 
Alvin Seiff. 1955. ii, 17p. diagrs., photos. 
(NACA Rept. 1222. Supersedes RM A52A24) 



NACA TRANSONIC WIND-TUNNEL TEST SECTIONS. 
Ray H. Wright and Vernon G. Ward. 1955. ii, 38p. 
diagrs., photos., tabs. (NACA Rept. 1231. Super- 
sedes RM L8J06) 



THEORETICAL AND EXPERIMENTAL INVESTIGA- 
TION OF THE EFFECT OF TUNNEL WALLS ON 
THE FORCES ON AN OSCILLATING AIRFOIL IN 
TWO-DLMENSIONAL SUBSONIC COMPRESSIBLE 
FLOW. Harry L. Runyan, Donald S. Woolston and 
A. Gerald Rainey. June 1955. 41p. diagrs., photo. 
(NACA TN 3416. Supersedes and extends 
RM L52I17a) 



INVESTIGATION OF THE EFFECT OF SHORT 
FIXED DIFFUSERS ON STARTING BLOWDOWN 
JETS IN THE MACH NUMBER RANGE FROM 2.7 
TO 4.5. John A. Moore. January 1956. 32p. 
diagrs., photos. (NACA TN 3545) 



EFFECT OF THICKNESS, CAMBER, AND THICK- 
NESS DISTRIBUTION ON AIRFOIL CHARACTERIS- 
TICS AT MACH NUMBERS UP TO 1.0. Bernard N. 
Daley and Richard S. Dick. March 1956. 75p. 
diagrs., photos., tab. (NACA TN 3607. Supersedes 
RM L52G31a) 



INVESTIGATION OF THE USE OF THE THERMAL 
DECOMPOSITION OF NITROUS OXIDE TO PRO- 
DUCE HYPERSONIC FLOW OF A GAS CLOSLY RE- 
SEMBLING AIR. Alexander P. Sabol and John S. 
Evans. March 1956. 36p. diagrs., tabs. 
(NACA TN 3624) 



INVESTIGATION OF BOUNDARY-LAYER TRANSI- 
TION ON 10° CONE IN LANGLEY 4- BY 4-FOOT 
SUPERSONIC PRESSURE TUNNEL AT MACH NUM- 
BERS OF 1.41, 1.61, AND 2.01. Archibald R. 
Sinclair and K. R. Czarnecki. May 1956. 17p. 
diagrs., photos. (NACA TN 3648) 



(9.1.2) 
FREE -FLIGHT 



FLIGHT INVESTIGATION TO DETERMINE THE 
HINGE MOMENTS OF A BEVELED-EDGE AILERON 
ON A 45° SWEPTBACK WING AT TRANSONIC AND 
LOW SUPERSONIC SPEEDS. William N. Gardner 
and Howard J. Curfman, Jr. November 12, 1947. 
20p. diagrs., photos. (NACA RM L7H26) 



ROCKET-POWERED FLIGHT TEST OF A ROLL- 
STABILIZED SUPERSONIC MISSILE CONFIGURA- 
TION. Robert A. Gardiner and Jacob Zarovsky. 
January 12, 1950. 32p. diagrs., photos., tab. 
(NACA RM L9K01a) 



FLIGHT INVESTIGATION OF A ROLL-STABILIZED 
MISSILE CONFIGURATION AT VARYING ANGLES 
OF ATTACK AT MACH NUMBERS BETWEEN 0,8 
AND 1.79. Jacob Zarovsky and Robert A. Gardiner. 
March 6, 1951. 38p. diagrs., photos., tab. 
(NACA RM L50H21) 



FLIGHT CALIBRATION OF ANGLE-OF-ATTACK 
AND SIDESLIP DETECTORS ON THE FUSELAGE 
OF A 35° SWEPT -WING FIGHTER AIRPLANE. 
Norman M. McFadden, George A. Rathert, Jr., and 
Richards. Bray. February 1952. 26p. diagrs., 
photos. (NACA RM A52A04) 



AN AIR-FLOW-DIRECTION PICKUP SUITABLE FOR 
TELEMETERING USE ON PILOTLESS AIRCRAFT. 
Wallace L. Ikard. March 1954. 25p. diagrs., 
photos. (NACA RM L53K16) 



WIND-TUNNEL INVESTIGATION OF A SHIELDED 
TOTAL-PRESSURE TUBE AT A MACH NUMBER OF 
1.61. Walter R. Russell and William Gracey. 
March 1954. 9p. diagrs., photo. (NACA 
RM L53L23a) 



A FREE-FLIGHT WIND TUNNEL FOR AERODY- 
NAMIC TESTING AT HYPERSONIC SPEEDS. 
Alvin Seiff. 1955. ii, 17p. diagrs., photos. 
(NACA Rept. 1222. Supersedes RM A52A24) 



FLIGHT CALIBRATION OF FOUR AIRSPEED SYS- 
TEMS ON A SWEPT-WING AIRPLANE AT MACH 
NUMBERS UP TO 1.04 BY THE NACA RADAR- 
PHOTOTHEODOLITE METHOD. Jim Rogers 
Thompson, Richard S. Bray, and George E . Cooper. 
November 1955. 41p. diagrs., photos., tab. 
(NACA TN 3526. Supersedes RM A50H24) 



WIND-TUNNEL INVESTIGATION OF A NUMBER OF 
TOTAL-PRESSURE TUBES AT HIGH ANGLES OF 
ATTACK. SUBSONIC, TRANSONIC, AND SUPER- 
SONIC SPEEDS. William Gracey. May 1956. 
30p. diagrs., tabs. (NACA TN 3641) 



200 



(9) RESEARCH EQUIPMENT AND TECHNIQUES 



(9.1.4) 
PROPULSION RESEARCH EQUIPMENT 



FREE-JET TESTS OF A 6.5-INCH-DIAMETER 
RAM-JET ENGINE AT MACH NUMBERS OF 1.81 
AND 2.00. Maxime A. Faget, Raymond S. Watson, 
and Walter A. Bartlett, Jr. March 7, 1951. 38p. 
diagrs., photos. (NACA RM L50L06) 

FREE-JET TESTS OF A 1.1-INCH-DIAMETER 
SUPERSONIC RAM-JET ENGINE. Joseph H. Judd 
and Otto F. Trout, Jr. March 1952. 24p. diagrs., 
photos., tabs. (NACA RM L51L18) 

TECHNIQUES FOR DETERMINING THRUST IN 
FLIGHT FOR AIRPLANES EQUIPPED WITH 
AFTERBURNERS. L. Stewart Rolls, C. Dewey 
Havill, and George R. Holden. January 1953. 27p. 
diagrs., photos. (NACA RM A52K12) 



ACOUSTICAL TREATMENT FOR THE NACA 8- BY 
6-FOOT SUPERSONIC PROPULSION WIND TUNNEL. 
Leo L. Beranek, Samuel Labate and Uno Ingard, 
Bolt Beranek and Newman, Inc. June 1955. 86p. 
diagrs., photo., 7 tabs. (NACA TN 3378) 

NOISE SURVEY OF A 10-FOOT FOUR-BLADE 
TURBINE -DRIVEN PROPELLER UNDER STATIC 
CONDITIONS. Max C. Kurbjun. July 1955. 25p. 
diagrs., photo. (NACA TN 3422) 



A SONIC-FLOW ORIFICE PROBE FOR THE IN- 
FLIGHT MEASUREMENT OF TEMPERATURE 
PROFILES OF A JET ENGINE EXHAUST WITH 
AFTERBURNING. C. Dewey Havill and L. Stewart 
Rolls. May 1956. 18p. diagrs., photos. 
(NACA TN 3714) 



(9.1.6) 
MATERIALS 



AXIAL-LOAD FATIGUE PROPERTIES OF 24S-T 
AND 75S-T ALUMINUM ALLOY AS DETERMINED 
IN SEVERAL LABORATORIES. H. J. Grover and 

W. S. Hyler, Battelle Memorial Institute, PaulKuhn 
and Charles B. Landers, Langley Aeronautical 
Laboratory and F. M. Howell, Aluminum Company 
of America. 1954. ii, 25p. diagrs., photos., 
7 tabs. (NACA Rept. 1190. Formerly TN 2928) 



PERFORATED SHEETS AS A POROUS MATERIAL 
FOR DISTRIBUTED SUCTION AND INJECTION. 
Robert E. Dannenberg, Bruno J. Gambucci, and 
James A. Weiberg. April 1956. 27p. diagrs., 
photos. (NACA TN 3669) 



(9.1.7) 
STRUCTURES 



CREEP AND CREEP-RUPTURE CHARACTERISTICS 
OF SOME RIVETED AND SPOT -WELDED LAP 
JOINTS OF AIRCRAFT MATERIALS. Leonard 
Mordfin, National Bureau of Standards. June 1955. 
53p. diagrs., photos., 6 tabs. (NACA TN 3412) 



RAPID RADIANT -HEATING TESTS OF MULTIWEB 
BEAMS. Joseph N. Kotanchik, Aldie E. Johnson, 
Jr., and Robert D. Ross. September 1955. 30p , 
diagrs., photos., tab. (NACA TN 3474) 



201 



(9) RESEARCH EQUIPMENT AND TECHNIQUES 



(9.2) 
Technique 



THE LONGITUDINAL STABILITY, CONTROL EF- 
FECTIVENESS, AND CONTROL HINGE-MOMENT 
CHARACTERISTICS OBTAINED FROM A FLIGHT 
INVESTIGATION OF A CANARD MISSILE CONFIG- 
URATION AT TRANSONIC AND SUPERSONIC 
SPEEDS. Roy J. Niewald and Martin T. Moul. 
November 24, 1950. 43p. diagrs., photos. 
(NACA RM L50I27) 

DYNAMIC STABILITY AND CONTROL CHARACTER- 
ISTICS OF A VERTICALLY RISING AIRPLANE 
MODEL IN HOVERING FLIGHT. William R. Bates, 
Powell M. Lovell, Jr., and Charles C. Smith, Jr. 
February 23, 1951. 16p. diagrs., photos., tab. 
(NACA RM L50J16) 

EFFECT OF THE PROXIMITY OF THE GROUND ON 
THE STABILITY AND CONTROL CHARACTERIS- 
TICS OF A VERTICALLY RISING AIRPLANE MODEL 
IN THE HOVERING CONDITION. Charles C. Smith, 
Jr., Powell M. Lovell, Jr., and William R. Bates. 
September 1951. 16p. diagrs., tab. (NACA 
RM L51G05) 



ADDITIONAL STUDIES OF THE STABILITY AND 
CONTROLLABILITY OF AN UNSWEPT-WING 
VERTICALLY RISING AIRPLANE MODEL IN 
HOVERING FLIGHT INCLUDING STUDIES OF VAR- 
IOUS TETHERED LANDING TECHNIQUES. 
William R. Bates, Powell M, Lovell, Jr., and 
Charles C. Smith, Jr. Movember 1951. 25p. 
diagrs., photos., tab. CNACA RM L5 1107a) 



IGNITION DELAY EXPERIMENTS WITH SMALL- 
SCALE ROCKET ENGINE AT SIMULATED ALTI- 
TUDE CONDITIONS USING VARIOUS FUELS WITH 
NITRIC ACID OXIDANTS. Dezso J. Ladanyi. 
January 1952. 44p. diagrs., photos., tabs. 
(NACA RM E51J01) 

A PRELIMINARY WIND-TUNNEL INVESTIGATION 
OF FLUTTER CHARACTERISTICS OF DELTA 
WINGS. Robert W. Herr. April 1952. 35p. 
diagrs., tabs. (NACA RM L52B14a) 



USE OF AN AERODYNAMICALLY PULSED ALL- 
MOVABLE HORIZONTAL TAIL TO OBTAIN LONGI- 
TUDINAL CHARACTERISTICS OF ROCKET- 
POWERED MODELS IN FREE FLIGHT AND SOME 
INITIAL RESULTS FROM AN ARROW-WING-BODY - 
TAIL CONFIGURATION. Warren Gillespie, Jr., and 
Albert E. Dietz. May 1952. 31p. diagrs., photos. 
(NACA RM L52C10) 

RESULTS OF TWO EXPERIMENTS ON FLUTTER 
OF HIGH-ASPECT-RATIO SWEPT WINGS IN THE 
TRANSONIC SPEED RANGE. W. T. Lauten, Jr. 
and Burke R. O 1 Kelly. July 1952. 22p. diagrs., 
photos., tabs. (NACA RM L52D24b) 

EFFECTS OF STABILIZING FINS AND A REAR- 
SUPPORT STING ON THE BASE PRESSURES OF A 
BODY OF REVOLUTION IN FREE FLIGHT AT 
MACH NUMBERS FROM 0.7 TO 1.3. Roger G. 
Hart. September 1952. 19p. diagrs., photos., tab. 
(NACA RM L52E06) 



INVESTIGATIONS AT SUPERSONIC SPEEDS OF THE 
BASE PRESSURE ON BODIES OF REVOLUTION 
WITH AND WITHOUT SWEPTBACK STABILIZING 
FINS. Eugene S. Love and Robert M. O'Donnell. 
December 1952. 66p. diagrs., photos. 
(NACA RM L52J21a) 

TECHNIQUES FOR DETERMINING THRUST IN 
FLIGHT FOR AIRPLANES EQUIPPED WITH 
AFTERBURNERS. L. Stewart Rolls, C. Dewey 
Havill, and George R. Holden. January 1953. 27p. 
diagrs., photos. (NACA RM A52K12) 

AN AUTOMATIC VISCOMETER FOR NON- 
NEWTONIAN MATERIALS. Ruth N. Weltmann and 
Perry W. Kuhns. August 1955. 34p. diagrs., 
photos., tab. (NACA TN 3510) 

ANALYSIS OF THE HORIZONTAL-TAIL LOADS 
MEASURED IN FLIGHT ON A MULTIENGINE JET 
BOMBER. William S. Aiken, Jr. and Bernard 
Wiener. September 1955. i, 69p. diagrs., photo., 
6 tabs. (NACA TN 3479) 

ACOUSTICS OF A NONHOMOGENEOUS MOVING 

MEDIUM. (Akustika Neodnorodnoi Dvizhushcheisya 
Sredy). D. I. Blokhintsev, February 1956. 194p. 
diagrs., photos. (NACA TM 1399. Trans, of 
Russian Book, 1946) 

INVESTIGATION OF THE USE OF THE THERMAL 
DECOMPOSITION OF NITROUS OXIDE TO PRO- 
DUCE HYPERSONIC FLOW OF A GAS CLOSLY RE- 
SEMBLING AIR. Alexander P. Sabol and John S. 
Evans. March 1956. 36p. diagrs., tabs. 
(NACA TN 3624) 

APPLICATION OF SCATTERING THEORY TO THE 
MEASUREMENT OF TURBULENT DENSITY FLUC- 
TUATIONS BY AN OPTICAL METHOD. Howard A. 
Stine and Warren Winovich. June 1956. 21p. diagrs., 
(NACA TN 3719) 



(9.2.1) 
CORRECTIONS 



LIFT AND PITCHING-MOMENT INTERFERENCE 
BETWEEN A POINTED CYLINDRICAL BODY AND 
TRIANGULAR WINGS OF VARIOUS ASPECT RATIOS 
AT MACH NUMBERS OF 1.50 AND 2.02. Jack N. 
Nielsen, Elliott D. Katzen, and Kenneth K. Tang. 
September 12, 1950. 53p. diagrs., photos., tabs. 
(NACA RM A50F06) 



FLIGHT CALIBRATION OF ANGLE-OF-ATTACK 
AND SIDESLIP DETECTORS ON THE FUSELAGE 
OF A 35° SWEPT -WING FIGHTER AIRPLANE. 
Norman M. McFadden, George A. Rathert, Jr., and 
RichardS. Bray. February 1952. 26p. diagrs., 
photos. (NACA RM A52A04) 



202 



(9) RESEARCH EQUIPMENT AND TECHNIQUES 



PRESSURE MEASUREMENTS ON A BODY OF REVO- 
LUTION IN THE LANGLEY 16-FOOT TRANSONIC 
TUNNEL AND A COMPARISON WITH FREE-FALL 
DATA. Joseph M. Hallissy, Jr. March 1952. I9p. 
diagrs. (NACA RM L51L07a) 



AN EXPERIMENTAL INVESTIGATION OF BOUND- 
ARY INTERFERENCE ON FORCE AND MOMENT 
CHARACTERISTICS OF LIFTING MODELS IN THE 
LANGLEY 16- AND 8- FOOT TRANSONIC TUNNELS. 
Charles F. Whitcomb and Robert S. Osborne. 
February 1953. 31p. photos., diagrs., tab. 
(NACA RM L52L29) 

COMPARISON OF LIFT-CURVE SLOPES FOR A 
MODEL TESTED IN TWO SLOTTED TUNNELS OF 
DIFFERENT SIZES AT HIGH SUBSONIC SPEEDS. 
Robert W. Boswinkie, Jr. June 1953. 13p. 
diagrs. (NACA RM L53E20a) 

AN INVESTIGATION OF A METHOD FOR OBTAIN- 
ING HYDRODYNAMIC DATA AT VERY HIGH 
SPEEDS WITH A FREE, WATER JET. Bernard 
Weinflash and John R McGehee. June 1954. 28p. 
diagrs., photos., i.abs. (NACA RM L54D23) 

THEORETICAL STUDY OF THE TUNNEL- 
BOUNDARY LIFT INTERFERENCE DUE TO 
SLOTTED WALLS IN THE PRESENCE OF THE 
TRAILING-VORTEX SYSTEM OF A LIFTING 
MODEL. Clarence W. Matthews. 1955. ii, 19p. 
diagrs. (NACA Rept. 1221. Supersedes 
RM L53A26) 

THEORETICAL AND EXPERIMENTAL INVESTIGA- 
TION OF THE EFFECT OF TUNNEL WALLS ON 
THE FORCES ON AN OSCILLATING AIRFOIL IN 
TWO-DIMENSIONAL SUBSONIC COMPRESSIBLE 
FLOW. Harry L. Runyan, Donald S. Woolston and 
A. Gerald Rainey. June 1955. 41p. diagrs., photo. 
(NACA TN 3416. Supersedes and extends 
RM L52I17a) 

PRACTICAL CONSIDERATIONS IN SPECIFIC 
APPLICATIONS OF GAS - FLOW INT ERFE ROME TRY. 
Walton L. Howes and Donald R. Buchele. July 1955. 
ii, 95p. diagrs., photos. (NACA TN 3507) 



AVERAGING OF PERIODIC PRESSURE PULSA- 
TIONS BY A TOTAL-PRESSURE PROBE. R. C. 
Johnson. October 1955. 30p. diagrs., photo., 
tabs. (NACA TN 3568) 



FLIGHT CALIBRATION OF FOUR AIRSPEED SYS- 
TEMS ON A SWEPT-WING AIRPLANE AT MACH 
NUMBERS UP TO 1.04 BY THE NACA RADAR- 
PHOTOTHEODOLITE METHOD. Jim Rogers 
Thompson, Richard S. Bray, and George E . Cooper. 
November 1955. 41p. diagrs., photos., tab. 
(NACA TN 3526. Supersedes RM A50H24) 

ERROR IN AIRSPEED MEASUREMENT DUE TO 
THE STATIC-PRESSURE FIELD AHEAD OF AN 
AIRPLANE AT TRANSONIC SPEEDS. Thomas C. 
O'Bryan, Edward C. B. Danforth, and J. Ford 
Johnston. February 1956. 13p. diagrs., photos. 
{NACA Rept. 1239. Supersedes RM L9C25; 
RM L50L28; RM L52A17) 



WIND-TUNNEL INVESTIGATION OF A NUMBER OF 
TOTAL-PRESSURE TUBES AT HIGH ANGLES OF 
ATTACK. SUBSONIC, TRANSONIC, AND SUPER- 
SONIC SPEEDS. William Gr^cey. May 1956. 
30p. diagrs., tabs. (NACA TN 3641) 



(9.2.2) 
AERODYNAMICS 



ROCKET-POWERED FLIGHT TEST OF A ROLL- 
STABILIZED SUPERSONIC MISSILE CONFIGURA- 
TION. Robert A. Gardiner and Jacob Zarovsky. 
January 12, 1950. 32p. diagrs., photos., tab. 
(NACA RM L9K01a) 

FLIGHT INVESTIGATION OF A ROLL-STABILIZED 
MISSILE CONFIGURATION AT VARYING ANGLES 
OF ATTACK AT MACH NUMBERS BETWEEN 0.8 
AND 1.79. Jacob Zarovsky and Robert A. Gardiner. 
March 6, 1951. 38p. diagrs., photos., tab. 
(NACA RM L50H21) 

WIND-TUNNEL INVESTIGATION AT SUBSONIC AND 
LOW TRANSONIC SPEEDS OF THE EFFECTS OF 
AILERON SPAN AND SPANWISE LOCATION ON THE 
ROLLING CHARACTERISTICS OF A TEST VEHICLE 
WITH THREE UNTAPERED 45° SWEPTBACK 
WINGS, HaroldS. Johnson. April 6, 1951. 26p. 
diagrs., photo., tab. (NACA RM L51B16) 



FLIGHT CALIBRATION OF ANGLE-OF-ATTACK 
AND SIDESLIP DETECTORS ON THE FUSELAGE 
OF A 35° SWEPT-WING FIGHTER AIRPLANE. 
Norman M. McFadden, George A. Rathert, Jr., and 
Richards. Bray. February 1952. 26p. diagrs., 
photos. (NACA RM A52A04) 



CHORDWISE PRESSURE DISTRIBUTION AT HIGH 
SUBSONIC SPEEDS NEAR MIDSEMISPAN OF A 
TAPERED 35° SWEPTBACK WING OF ASPECT 
RATIO 4 HAVING NACA 65A006 AIRFOIL SECTIONS 
AND EQUIPPED WITH VARIOUS SPOILER AILER- 
ONS. Alexander D. Hammond and Barbara M. 
McMullan. June 1952. 76p. diagrs., tabs. 
(NACA RM L52C28) 



AN EXPERIMENTAL INVESTIGATION OF BOUND- 
ARY INTERFERENCE ON FORCE AND MOMENT 
CHARACTERISTICS OF LIFTING MODELS IN THE 
LANGLEY 16- AND 8-FOOT TRANSONIC TUNNELS. 
Charles F. Whitcomb and Robert S. Osborne. 
February 1953. 31p. photos., diagrs., tab. 
(NACA RM L52L29) 



THE EFFECT AT HIGH SUBSONIC SPEEDS OF A 
FLAP-TYPE AILERON ON THE CHORDWISE PRES- 
SURE DISTRIBUTION NEAR MIDSEMISPAN OF A 
TAPERED 35° SWEPTBACK WING OF ASPECT 
RATIO 4 HAVING NACA 65A006 AIRFOIL SECTION. 
Alexander D. Hammond and Barbara M. Keffer. 
May 1953. 89p. diagrs., tab. (NACA RM L53C23) 



SLOTTED-BOUNDARY INTERFERENCE EFFECTS 
ON WEDGE AIRFOILS AT LOW SUPERSONIC MACH 
NUMBERS. William J. Nelson and Allen R. Vick. 
July 1953. 27p. diagrs., photos. 
(NACA RM L53F11) 

EFFECT OF VARIABLE VISCOSITY AND THERMAL 
CONDUCTIVITY ON HIGH-SPEED SLIP FLOW BE- 
TWEEN CONCENTRIC CYLINDERS. T. C. Lin and 
R. E. Street, University of Washington. 1954. ii, 
36p. diagrs. (NACA Rept. 1175. Formerly 
TN 2895) 



203 



(9) RESEARCH EQUIPMENT AND TECHNIQUES 



APPLICATION OF SEVERAL METHODS FOR DE- 
TERMINING TRANSFER FUNCTIONS AND FRE- 
QUENCY RESPONSE OF AIRCRAFT FROM FLIGHT 
DATA. John M. Eggleston and Charles W, 
Mathews, 1954. li, 24p. diagrs., tabs. 
(NACA Rept. 1204. Supersedes TN 2997) 



DEVELOPMENT OF TURBULENCE-MEASURING 
EQUIPMENT. Leslie S. G. Kovasznay, John 
Hopkins University. 1954. ii, 30p. diagrs., 
photos., tab. (NACA Rept. 1209. Supersedes 
TN 2839) 



A SUMMARY OF INFORMATION ON SUPPORT 
INTERFERENCE AT TRANSONIC AND SUPERSONIC 
SPEEDS. Eugene S. Love. January 1954. 26p. 
diagrs. (NACA RM L53K12) 



EFFECT OF GROUND INTERFERENCE ON THE 
AERODYNAMIC AND FLOW CHARACTERISTICS OF 
A 42° SWEPTBACK WING AT REYNOLDS NUMBERS 
UP TO 6.8 x 10 6 . G. Chester Furlong and Thomas 
V. Bollech. 1955. ii, 60p. diagrs., photos., tab. 
(NACA Rept. 1218. Combination of RM L8G22; 
TN 2487) 



A FREE- FLIGHT WIND TUNNEL FOR AERODY- 
NAMIC TESTING AT HYPERSONIC SPEEDS. 
AlvinSeiff. 1955. li, 17p. diagrs., photos. 
(NACA Rept. 1222. Supersedes RM A52A24) 



RECOVERY AND TIME-RESPONSE CHARACTER- 
ISTICS OF SDC THERMOCOUPLE PROBES IN SUB- 
SONIC AND SUPERSONIC FLOW. Truman M. 
Stickney. July 1955. 25p. diagrs., photos., 2 tabs. 
(NACA TN 3455) 



PRACTICAL CONSIDERATIONS IN SPECIFIC 
APPLICATIONS OF GAS-FLOW INTER FEROMETRY. 
Walton L. Howes and Donald R. Buchele. July 1955. 
ii, 95p. diagrs., photos. (NACA TN 3507) 



MEASUREMENTS OF TURBULENT SKIN FRICTION 
ON A FLAT PLATE AT TRANSONIC SPEEDS. 

Raimo J(aakko) Hakkinen, Caliiornia Institute of 
Technology. September 1955. 41p. diagrs. , photo, 

tabs. (NACA TN 3486) 



VISUALIZATION STUDY OF SECONDARY FLOWS 
IN TURBINE ROTOR TIP REGIONS. Hubert W. 
Allen and Milton G. Kofskey. September 1955. 
33p. diagrs., photos., tab. (NACA TN 3519) 



INTENSITY, SCALE, AND SPECTRA OF TURBU- 
LENCE IN MIXING REGION OF FREE SUBSONIC 
JET. James C. Laurence. September 1955. 58p. 
diagrs., photo., tab. (NACA TN 3561) 



AVERAGING OF PERIODIC PRESSURE PULSA- 
TIONS BY A TOTAL -PRESSURE PROBE. R. C. 
Johnson. October 1955. 30p. diagrs., photo., 
tabs. (NACA TN 3568) 



AN EXPERIMENTAL COMPARISON OF THE 
LAGRANGIAN AND EULERIAN CORRELATION 
COEFFICIENTS IN HOMOGENEOUS ISOTROPIC 
TURBULENCE. William R. Mickelsen. October 
1955. 42p. diagrs. (NACA TN 3570) 



A PRELIMINARY INVESTIGATION OF THE EF- 
FECTS OF FREQUENCY AND AMPLITUDE ON THE 
ROLLING DERIVATIVES OF AN UNSWEPT-WING 
MODEL OSCILLATING IN ROLL. Lewis R. Fisher, 
Jacob H. Lichtenstein, and Katherine D. Williams. 
January 1956. 29 p. diagrs., photos. 
(NACA TN 3554) 



A METHOD FOR CALCULATING THE CONTOUR OF 
BODIES OF REVOLUTION WITH A PRESCRIBED 
PRESSURE GRADIENT AT SUPERSONIC SPEED 
WITH EXPERIMENTAL VERIFICATION. Paige B. 
Burbank. March 1956. 64p. diagrs., photos., 
tabs. (NACA TN 3555) 



AN EVALUATION OF FOUR EXPERIMENTAL 
METHODS FOR MEASURING MEAN PROPERTIES 
OF A SUPERSONIC TURBULENT BOUNDARY 
LAYER. George J. Nothwang. June 1956. 34p. 
diagrs., photos. (NACA TN 3721) 



(9.2.3) 
HYDRODYNAMICS 

AN INVESTIGATION OF A METHOD FOR OBTAIN- 
ING HYDRODYNAMIC DATA AT VERY HIGH 
SPEEDS WITH A FREE WATER JET. Bernard 
Weinflash and John R. McGehee. June 1954. 28p. 
diagrs., photos., tabs. (NACA RM L54D23) 



(9.2.4) 
LOADS AND CONSTRUCTION 

CALIBRATION OF STRAIN-GAGE INSTALLATIONS 
IN AIRCRAFT STRUCTURES FOR THE MEASURE- 
MENT OF FLIGHT LOADS. T. H. Skopinski, 
William S. Aiken, Jr. and Wilber B. Huston. 1954. 
ii, 29p. diagrs., 10 tabs. (NACA Rept. 1178. 
Formerly TN 2993; RM L52G31) 



CREEP AND CREEP-RUPTURE CHARACTERISTICS 
OF SOME RIVETED AND SPOT -WELDED LAP 
JOINTS OF AIRCRAFT MATERIALS. Leonard 
Mordfin, National Bureau of Standards. June 1955. 
53p. diagrs., photos., 6 tabs. (NACA TN 3412) 



A METHOD FOR OBTAINING STATISTICAL DATA 
ON AIRPLANE VERTICAL VELOCITY AT GROUND 
CONTACT FROM MEASUREMENTS OF CENTER- 
OF-GRAVITY ACCELERATION. Robert C. Dreher. 
February 1956. 21p. diagrs., photo., tabs. 
(NACA TN 3541) 



INTERIM REPORT ON FATIGUE CHARACTERISTICS 
OF A TYPICAL METAL WING. J. L. Kepert and 
A. O. Payne. March 1956. 80p. diagrs., photos., 
tabs. (NACA TM 1397. Originally issued as Report 
ARL/SM. ?07, Aeronautical Research Laboratories, 
Australia) 



2 04 



(9) RESEARCH EQUIPMENT AND TECHNIQUES 



(9.2.5) 
PROPULSION 



FREE-JET TESTS OF A 6.5-INCH-DIAMETER 
RAM-JET ENGINE AT MACH NUMBERS OF 1.81 
AND 2.00. Maxime A. Faget, Raymonds. Watson, 
and Walter A. Bartlett, Jr. March 7, 1951. 38p. 
diagrs., photos. (NACA RM L50L06) 

PROPAGATION OF A FREE FLAME IN A TURBU- 
LENT GAS STREAM. William R. Mickelsen and 
Norman E. Ernstein. July 1955. 89p. diagrs., 
photos., 2 tabs. (NACA TN 3456) 

THE EFFECTIVENESS OF WING VORTEX GENERA- 
TORS IN IMPROVING THE MANEUVERING CHARAC- 
TERISTICS OF A SWEPT -WING AIRPLANE AT 
TRANSONIC SPEEDS. Norman M. McFadden, 
George A. Rathert, Jr. , and Richard S. Bray. 
September 1955. 43p. diagrs. , photos. , tab. 
(NACA TN 3523. Supersedes RM A51J18) 

A POLAR-COORDINATE SURVEY METHOD FOR 
DETERMINING JET-ENGINE COMBUSTION- 
CHAMBER PERFORMANCE. Robert Friedman and 
Edward R. Carlson. September 1955. 29p. 
diagrs., photo., tab. (NACA TN 3566) 

AVERAGING OF PERIODIC PRESSURE PULSA- 
TIONS BY A TOTAL-PRESSURE PROBE. R. C. 
Johnson. October 1955. 30p. diagrs., photo., 
tabs. (NACA TN 3568) 

A SONIC-FLOW ORIFICE PROBE FOR THE IN- 
FLIGHT MEASUREMENT OF TEMPERATURE 
PROFILES OF A JET ENGINE EXHAUST WITH 
AFTERBURNING. C. Dewey Havill and L. Stewart 
Rolls. May 1956. 18p. diagrs., photos. 
(NACA TN 3714) 

(9.2.6) 
OPERATING PROBLEMS 

AERODYNAMIC MEASUREMENTS MADE DURING 
NAVY INVESTIGATION OF HUMAN TOLERANCE 
TO WIND BLASTS. Donald L. Loving. March 11, 
1947. 34p. diagrs., photos., 2 tabs. (NACA 
RM L7C25) 



AN EXPERIMENTAL INVESTIGATION OF THE 
TRANSONIC-FLOW-GENERATION AND SHOCK 
WAVE -RE FLECTION CHARACTERISTICS OF A 
TWO-DIMENSIONAL WIND TUNNEL WITH 17- 
PERCENT-OPEN PERFORATED WALLS. Don D. 
Davis. Jr., Thomas B. Sellers, and George M. Stokes. 
April 1954. 40p. diagrs., photos. 
(NACA RM L54B15a) 

PERFORMANCE AND OPERATIONAL STUDIES OF 
A FULL-SCALE JET- ENGINE THRUST REVERSER. 
Robert C. Kohl. April 1956. 38p. diagrs., photo. 
(NACA TN 3665) 



(9.2.7) 
MATHEMATICS 



ROCKET-POWERED FLIGHT TEST OF A ROLL- 
STABILIZED SUPERSONIC MISSILE CONFIGURA- 
TION. Robert A. Gardiner and Jacob Zarovsky. 
January 12, 1950. 32p. diagrs., photos., tab. 
(NACA RM L9K01a) 



APPLICATION OF SEVERAL METHODS FOR DE- 
TERMINING TRANSFER FUNCTIONS AND FRE- 
QUENCY RESPONSE OF AIRCRAFT FROM FLIGHT 
DATA. John M. Eggleston and Charles W. 
Mathews. 1954. II, 24p. diagrs., tabs. 
(NACA Rept. 1204. Supersedes TN 2997) 



THEORETICAL AND ANALOG STUDIES OF THE 
EFFECTS OF NONLINEAR STABILITY DERIVA- 
TIVES ON THE LONGITUDINAL MOTIONS OF AN 
AIRCRAFT IN RESPONSE TO STEP CONTROL 
DEFLECTIONS AND TO THE INFLUENCE OF PRO- 
PORTIONAL AUTOMATIC CONTROL. Howard J. 
Curfman, Jr. 1955. 11, 21p. diagrs. (NACA 
Rept. 1241. Supersedes RM L50L11) 



A COMPARISON OF TWO METHODS FOR COMPUT- 
ING THE WAVE DRAG OF WING-BODY COMBINA- 
TIONS. Alberta Alksne. April 1955. 32p. diagrs. 
(NACA RM A55A06a) 



MAXIMUM THEOREMS AND REFLECTIONS OF 
SIMPLE WAVES. P. Germain, Brown University. 
June 1955. 22p. (NACA TN 3299) 



PRACTICAL CONSIDERATIONS IN SPECIFIC 
APPLICATIONS OF GAS-FLOW INTERFEROMETRY. 
Walton L. Howes and Donald R. Buchele. July 1955. 
ii, 95p. diagrs., photos. (NACA TN 3507) 



EXTRAPOLATION TECHNIQUES APPLIED TO 
MATRDC METHODS IN NEUTRON DIFFUSION 
PROBLEMS. Robert R. McCready. July 1955. 
diagrs. (NACA TN 3511) 



32p. 



FROM LINEAR MECHANICS TO NONLINEAR 
MECHANICS. (De la mecanique line'aire a la 
mecanique non lineaire). Julien Loeb. October 
1955. 18p, diagrs.^ ^NACA TM 1396. Trans, 
from Annales des Telecommunications, v. 5, no. 2, 
Feb., 1950, p. 65-71) 



SOUND PROPAGATION INTO THE SHADOW ZONE 
IN A TEMPERATURE-STRATIFIED ATMOSPHERE 
ABOVE A PLANE BOUNDARY. David C. Pridmore- 
Brown and Uno Ingard, Massachusetts Institute of 
Technology. October 1955. 57p. diagrs., photo. 
(NACA TN 3494) 



METHOD AND TABLES FOR DETERMINING THE 
TIME RESPONSE TO A UNIT IMPULSE FROM 
FREQUENCY-RESPONSE DATA AND FOR DETER- 
MINING THE FOURIER TRANSFORM OF A FUNC- 
TION OF TIME. C&rl R. Huss and James J. 
Donegan. January 1956. 38p. diagrs., tabs. 
(NACA TN 3598) 



ON THE INSTABILITY OF METHODS FOR THE 
INTEGRATION OR ORDINARY DIFFERENTIAL 
EQUATIONS, (tiber die Instabilitat von Methoden 
zur Integration gewohnlicher Differentialgleichungen). 
Heinz Rutishauser. Aprif 1956. 15p. 
(NACA TM 1403. Trajjs. trom Zeitschrift fur 
angewandte Mathematik und Physik, v. 3, 1952, 
p.65-74) 



(12) 



(12) 
TECHNICAL SUMMARIES 



205 



V 



(12) TECHNICAL SUMMARIES 



(12) 
TECHNICAL SUMMARIES 



SUMMARY OF SCALE -MODEL THRUST -REVERSER 
INVESTIGATION. John H. Povolny, Fred W. 
Steffen, and Jack G. McArdle. February 1956. 
49p. diagrs., photos. (NACA TN 3664) 

THERMODYNAMIC PROPERTIES OF GASEOUS 
NITROGEN. Harold W. Woolley, National Bureau 
of Standards. March 1956. 114p. diagrs,, tabs. 
(NACA TN 3271) 



GENERALIZED TABLES OF CORRECTIONS TO 
THERMODYNAMIC PROPERTIES FOR NONPOLAR 
GASES. Harold W. Woolley and William S. Benedict, 
National Bureau of Standards. March 1956. 62p. 
diagrs., tabs. (NACA TN 3272) 



ALPHABETICAL SUBJECT INDEX 



UBJECT 

INDEX 



207 



Subject Heading Outline 



Accessories and Accessory Functions 
See also 

Fuel Systems 

Ignition Systems 

Starting Systems 
Adhesives 
Aerodynamics 
See also 

Aerodynamics, Fundamental 

Aeroelasticity 

Aircraft 

Bodies 

Internal Aerodynamics 

Propellers 

Stability and Control 

Wings 

Wings, Rotating 
Aerodynamics, Fundamental 
See also 

Aerodynamics with Heat 

Flow, Compressible 

Flow, Incompressible 

Flow of Rarefied Gases 

Flow, Viscous 
Aerodynamics with Heat 
See also 

Heat, Additions of - Aerodynamic 

Heat Transfer, Aerodynamic 

Heating, Aerodynamic 
Aeroelasticity 

Air Brakes (1 

Air Inlets 
See also 

Air Inlets - Nose, Annular 

Air Inlets - Nose, Central 

Air Inlets, Side 

Air Inlets - Wing-Leading-Edge 
Air Inlets - Central, Subsonic (1.4. 

Air Inlets - Central, Supersonic (1.4. 

Air Inlets - Nose, Annular (1. 

Air Inlets - Nose, Central (1. 

See also 

Air Inlets - Central, Subsonic 

Air Inlets - Central, Supersonic 

Air Inlets - Propeller -Spinner -Cowl 
Air Inlets -Propeller -Spinner -Cowl (1.4. 

.4. 
(1. 



Subject 




Subject 


Heading 




Heading 


Number 


Subject Heading Outline 

Missiles 
Rotating-Wing Aircraft 


Number 


(3. 12) 


Airplanes 
See also 


(1.7.1) 




Airplanes - Components in Combination 




Airplanes - Performance 






Airplanes - Specific Types 




(5.1.8) 


Airplanes - Components in 




(1) 


Combination 
See also 
External Stores - Effects of - 

Airplanes 
Propeller and Jet Combinations - 
Airplanes 


(1.7.1.1) 




Tail-Wing- Fuselage Combinations 


- 




Airplanes 






Wing-Fuselage Combinations - 






Airplanes 






Wing-Nacelle Combinations - 




(1.1) 


Airplanes 






Airplanes - Performance 


(1.7.1.3) 




Airplanes - Specific Types 


(1.7.1.2) 




Alloys, Heat-Resisting 


(5.1.4) 




Aluminum 


(5.1.1) 




Atmosphere 


(6.1) 




See also 




(1.1.4) 


Gusts, Atmospheric 
Standard Atmosphere 






Autogiros 


(1.7.3.1) 


(1.9) 


B 




L. 8. 2.4) 


Beams, Box 


(4.3.4.1) 


(1.4.1) 


Beams, Structural 


(4.3.4) 



Air Inlets, Scoop (1 

Air Inlets, Side 
See also 

Air Inlets, Scoop 

Air Inlets, Submerged 
Air Inlets, Submerged (1 

Air Inlets, Wing-Leading-Edge 
Aircraft 
See also 

Airplanes 

Biplanes and Tripianes 



1.1.2) 
1.1.3) 
4.1.2) 
4.1.1) 



1.1.1) 
1.4.1) 
4.1.4) 



1.4.2) 

4.1.3) 

(1.7) 



See also 

Beams, Box 
Bearings, Sleeve 
Bends 

Biplanes and Tripianes 
Blade Sections - Propellers 
Bodies 
See also 

Bodies - Aerodynamic Theory 

Bodies, Ducted 

Bodies - Shape Variables 

Canopies 
Bodies - Aerodynamic Theory 
Bodies - Cross Section 
Bodies, Ducted 
See also 

Bodies, Ducted - Nose Shape 

Exits, Side - Ducted Bodies 

Inlets, Side - Ducted Bodies 
Bodies, Ducted - Nose Shape 
Bodies - Fineness Ratio 
Bodies - Shape Variables 
See also 

Bodies - Cross Section 

Bodies - Fineness Ratio 



(3.8.2.1) 

(1.4.2.4) 

(1.7.6) 

(1.5.2.1) 

(1.3) 



(1.3.1) 

(1.3.2.2) 

(1.3.4) 



(1.3.4.1) 

(1.3.2.1) 

(1.3.2) 



208 



Subject Heading Outline 



Subject 

Heading 

Number 



.3.2.4) 

.3.2.3) 

(3-3) 

(3.3.2) 



.2.8.1) 

.4.7.1) 

.1.6.1) 
2. 2. 8) 



Bodies - Surface Conditions 
Bodies - Thickness Distribution 
Protuberances - Bodies 
Bodies - Surface Conditions (1 

Bodies - Thickness Distribution (1 

Booster Systems, Auxiliary 
Booster Systems, Auxiliary - Gas 

Turbines 
See also 
Turbines, Gas - Afterburning 
Turbines, Gas - Bleedoff 
Turbines, Gas - Liquid Injection 
Boundary-Layer Characteristics - 

Complete Wings (1. 2 
Boundary-Layer Characteristics - 

Internal Aerodynamics (1 

Boundary-Layer Characteristics - 

Wing Sections (1. 2 
Boundary Layer - Complete Wings (1. 

See also 
Boundary-Layer Characteristics - 

Complete Wings 
Boundary-Layer Control - Complete 

Wings 
Boundary-Layer Control - Complete 

Wings (1.2 
Boundary-Layer Control - Internal 

Aerodynamics (1 
Boundary-Layer Control - Wing 

Sections (1. 2 

Boundary Layer - Internal 
Aerodynamics 
See also 
Boundary-Layer Characteristics - 

Internal Aerodynamics 
Boundary-Layer Control - Internal 
Aerodynamics 
Boundary Layer - Wing Sections (1. 2. 1. 6) 

See also 
Boundary-Layer Characteristics - 

Wing Sections 
Boundary-Layer Control - Wing 
Sections 
Boxes, Structural (4.3.5.2) 



Canopies (1.3.3) 

Cascades (1.4.5) 

Cascades - Experiment (1.4.5.2) 

Cascades - Theory (1.4. 5. 1) 

Ceramals ( 5 - 1- 12 ) 

Ceramics (5. 1. 5) 

Columns, Structural (4.3.1) 

Combustion and Combustors (3. 5) 
See also 
Combustion - Effect of Engine 

Operating Conditions and 

Combustion-Chamber 



.2.8.2) 
.4.7.2) 
.1.6.2) 
(1.4.7) 



Subject Heading Outline 

Geometry 
Combustion Research - General 
Combustion - Effect of Engine Operating 
Conditions and Combustion-Chamber 
Geometry 
See also 
Combustion - Ram-Jet Engines 
Combustion - Rocket Engines 
Combustion - Turbine Engines 
Combustion - Effects of Fuel 
Atomization 
Combustion - Ignition of Gases 
Combustion, Laminar-Flow 
Combustion - Ram-Jet Engines 
Combustion - Reaction Mechanisms 
Combustion Research - General 
See also 
Combustion - Effects of Fuel 
Atomization 
- Ignition of Gases 
Laminar -Flow 
Reaction Mechanisms 
Turbulent-Flow 
Rocket Engines 
Turbine Engines 



Subject 

Heading 

Number 



(3.5.2) 



(3.5. 
(3.5. 
(3.5. 
(3.5. 
(3.5. 
(3. 



1.4) 
1.6) 

1.1) 
2.3) 
1.5) 
5.1) 



Combustion 
Combustion, 
Combustion 
Combustion, 

Combustion 

Combustion 



Combustion, Turbulent-Flow 
Compression and Compressors 
Compressor Flow - Theory and 
Experiment 



(3.5 
(3.5 
(3.5 



Compressors 
Compressors 
Compressors 
Compressors 
Connections 



- Axial-Flow 

- Mixed- Flow 

- Radial-Flow 

- Stress and Vibration 
Bonded 



Connections, Riveted 
Connections, Structural 
See also 
Connections, Bonded 
Connections, Riveted 
Connections, Welded 
Connections, Welded 
Contact Surfaces, Sliding 
See also 
Bearings, Sleeve 
Control 
See also 
Air Brakes 
Control, Automatic 
Control, Directional 
Control, Hinge Moment 
Control, Lateral 
Control, Longitudinal 
Controls, All-Movable - Complete 

Wings 
Controls - Complete Wings 
Controls, Flap-Type - Complete 

Wings 
Controls, Flap-Type - Wing 
Sections 



(3 
(3.6 
(3.6 
(3.6 

(3 
(4.3 
(4.3 

(4 



.2.5) 
.2.2) 
.1.2) 
(3.6) 

.6.1) 

.1.1) 

.1.3) 

.1.2) 

.6.2) 

6.4) 

6.2) 

3.6) 



(4.3. 
(3. 



6.3) 
8.2) 



(1.8.2) 



(1.8. 
(1.8. 
(1.8. 
(1.8. 
(1.8. 

(1.2.2. 
(1.2 



2.6) 
2.3) 
2.5) 
2.2) 
2.1) 

4.3) 
2.4) 



(1.2.2.4.1) 
(1.2.1.5.1) 



209 



Subject Heading Outline 

Controls, Spoiler - Complete 
Wings 
Controls, Spoiler - Wing 
Sections 
Controls - Wing Sections 
See also 
Controls, Flap-Type - Wing 
Sections 
Controls, Spoiler - Wing 
Sections 
Cooling - Gas -Turbine Systems 
Cooling - Ram Jets 
Cylinders 
See also 
Cylinders, Structural - Circular 
Cylinders, Structural - Circular 



Subject 

Heading 

Number 



(1.2.2.4.2) 

(1.2.1.5.2) 
(1.2.1.5) 



Subject Heading Outline 



Subject 
Heading 

Number 



(3. 10. 2) 

(3. 10. 3) 

(4.3.5.1) 



(4.3.5.1.1) 



(1.8.1.2.3) 
(1.4.2.1) 
(1.4.2.1.1) 
(1.4.2.1.2) 
(1.2.2,2,7) 
(1.4.2) 



(3.2) 



Damping Derivatives - Stability 
Diffusers 

Diffusers, Subsonic 
Diffusers, Supersonic 
Dihedral - Complete Wings 
Ducts 
See also 

Bends 

Diffusers 

Nozzles 

Pipes 



Engines - Control 
Engines - Control - Turbine- 
Propeller 
Engines - Control - Turbojet 
Engines - Cooling 
See also 

Cooling - Gas-Turbine Systems 

Cooling - Ram Jets 
Engines, Pulse-Jet 
Engines, Ram-Jet 
Engines, Reciprocating 
Engines, Rocket 
Engines, Turbojet 
Engines, Turbo-Propeller 
Exits 

Exits, Side - Ducted Bodies 
External Stores - Effects of - 
Airplanes 



Fans 

Fire Hazards 

Flaps, Leading-Edge - Complete 

Wings (1.2.2.3.3) 
Flaps, Trailing-Edge - Complete 

Wings (1.2.2.3.1) 



(3.2.4) 

(3. 2. 2) 

(3. 10) 


(3.1.6) 
(3.1.7) 
(3.1.1) 
(3.1.8) 
(3.1.3) 
(3.1.4) 
(1.4.3) 
(1.3.4.4) 


(1.7.1.1.5) 


(1.4.6) 
(7.9) 



Flow, Compressible (1. 1. 2) 

See also 
Flow, Mixed 
Flow, Subsonic 
Flow, Supersonic 
Flow, Incompressible (1.1.1) 

Flow - Jet-Mixing (1. 1. 3. 3) 

Flow, Laminar (1.1.3.1) 

Flow, Mixed (1.1.2.2) 

Flow of Rarefied Gases (1. 1. 5) 

Flow, Slip (1.1.5.1) 

Flow, Subsonic (1. 1. 2. 1) 

Flow, Supersonic (1.1.2.3) 

Flow, Turbulent (1.1.3.2) 

Flow, Viscous (1. 1.3) 

See also 
Flow - Jet-Mixing 
Flow, Laminar 
Flow, Turbulent 
Flying Qualities (1. 8. 5) 

Friction and Lubrication (3. 8) 

See also 
Contact Surfaces - Sliding 
Friction and Lubrication - Theory 
and Experiment 
Lubricants 

Surfaces, Contact - Sliding and 
Rolling 
Friction and Lubrication - Hydro- 
dynamic Theory (3. 8. 1. 1) 
Friction and Lubrication - Surface 

Conditions (3.8.1.3) 

Friction and Lubrication - Theory 

and Experiment (3. 8. 1) 

See also 
Friction and Lubrication - Hydro- 
dynamic Theory 
Friction and Lubrication - Surface 
Conditions 
Lubrication, Chemistry 
Fuel Systems (3. 12. 1) 

Fuel Systems - Engines, Pulse-Jet (3. 12. 1. 6) 
Fuel Systems - Engines, Ram-Jet (3. 12. 1. 7) 
Fuel Systems - Engines, Rocket (3. 12. 1.8) 

Fuel Systems - Engines, Turbojet (3. 12. 1.4) 
Fuels (3.4) 

Fuels - Preparation (3. 4. 1) 

Fuels - Properties, Physical and 

Chemical (3.4.2) 

Fuels - Relation to Engine Performance (3. 4. 3) 
Fuels - Rockets (Includes Fuel and 

Oxidant) (3.4.3.3) 
Fuels - Turbine Engines, Ram-Jets, 

and Pulse-Jets (3. 4. 3. 2) 



Gases, Kinetic - Properties (3.11.1) 

Gases, Properties (3. 11) 

Gases, Thermodynamic - Properties (3.11.2) 



Z1U 





Subject 




Heading 


Subject Heading Outline 


Number 


Gears 


(3.8.4.1) 


Gusts - Alleviation 


(6.1.2.4) 


Gusts, Atmospheric 


(6.1.2) 


Gusts - Frequency 


(6.1.2.2) 


Gusts - Structure 


(6.1.2.1) 


Gusts - Turbulence 


(6.1.2.3) 


H 

Heat, Additions of - Aerodynamic 


(1.1.4.3) 


Heat Exchangers 


(3.9.2) 


See also 




Regenerators 




Heat Transfer 


(3.9) 


See also 




Heat Exchangers 




Heat Transfer - Theory and 




Experiment 




Heat Transfer - Aerodynamic 


(1.1.4.2) 


Heat Transfer - Cascades 


(3.9.1.1) 


Heat Transfer - Theory and 




Experiment 


(3.9.1) 


See also 




Heat Transfer - Cascades 




Heating, Aerodynamic 


(1.1.4.1) 


Helicopters 


(1.7.3.2) 


High-Lift Devices -Complete 




Wings 


(1.2.2.3) 


See also 




Flaps, Leading-Edge - Complete 




Wings 




Flaps, Trailing-Edge - Complete 




Wings 




Slots and Slats - Complete Wings 




Hull Variables - Seaplane 


(2.3) 


Hulls, Seaplane - Chines 


(2.3.6) 


Hulls, Seaplane - Dead Rise 


(2. 3. 2) 


Hulls, Seaplane - Forebody Shape 


(2. 3. 5) 


Hulls, Seaplane - Length-Beam Ratio 


(2.3.1) 


Hydrodynamic Configurations - General 


Studies (2. 2) 


Hydrodynamic Theory 


(2.1) 


Hydrodynamics 


(2) 


See also 




Hull Variables - Seaplane 




Hydrodynamic Configurations - General 


Studies 


Hydrodynamic Theory 




Hydrofoils 




Planing Surfaces, Hydrodynamic 




Stability and Control - Hydrodynamics 


Surface Craft 




Hydrofoils 

I 


(2.7) 


Ice Formation 


(6.2) 


Ice Prevention and Removal 


(7.3) 



Subject Heading Outline 



Subject 

Heading 

Number 



(7.3.1) 

(7.3.2) 

(7.3.6) 

(7.3.4) 

(7.3.3) 

(3.12.2) 

(1.2.2.2.5) 

(1.3.4.3) 

(8) 

(8.1) 

(8.2) 

(8.3) 

(1.7.2.1.3) 

(1.5.2.8) 

(1.4) 



Ice Prevention and Removal - Accesso- 
ries, Miscellaneous (7. 3. 5) 



Ice Prevention and Removal - Engine 
Induction Systems 
Ice Prevention and Removal - 

Propellers 
Ice Prevention and Removal - 

Propulsion Systems 
Ice Prevention and Removal - 

Windshields 
Ice Prevention and Removal - Wings 

and Tails 
Ignition Systems 

Inlets and Exits - Complete Wings 
Inlets, Side - Ducted Bodies 
Instruments 
Instruments, Flight 
Instruments, Laboratory 
Instruments, Meteorological 
Interference, Jet - Missiles 
Interference of Bodies - Propellers 
Internal Aerodynamics 
See also 
Air Inlets 

Boundary Layer - Internal Aerodynamics 
Cascades 
Ducts 
Exits 
Fans 
Pumps, Jet and Thrust Augmentors 



Loads (4. 1) 

See also 
Loads, Aerodynamic 
Loads, Landing 
Loads, Aerodynamic (4. 1. 1) 

See also 

Loads, Aerodynamic - Tail 
Loads, Aerodynamic - Wings 
Loads - Aeroelasticity 
Loads - Fuselages, Nacelles, and 

Canopies 
Loads - Rotating Wings 
Loads, Aerodynamic - Tail (4. 1. 1. 2) 

See also 

Loads, Buffeting and Gust - Tail 
Loads, Maneuvering - Tail 
Loads, Steady - Tail 
Loads, Aerodynamic - Wings (4. 1. 1. 1) 

See also 
Loads, Buffeting - Wings 
Loads, Gust - Wings 
Loads, Maneuvering - Wings 
Loads, Steady - Wings 
Loads - Aeroelasticity (4. 1. 1. 5) 

Loads and Construction, Aircraft (4) 

See also 
Loads 
Structures 
Vibration and Flutter 



211 



Loads and Stresses, 
Loads and Stresses, 



Subject Heading Outline 

Loads and Stresses, Structural 
Loads and Stresses, Structural - 

Bending 
Loads and Stresses, Structural - 

Compression 
Loads and Stresses, Structural - 

Concentrated 
Loads and Stresses, Structural - 

Dynamic 
Loads and Stresses, Structural - 

Repeated Dynamic 
Loads and Stresses, Structural - 

Shear 
Structural - 

Tension 
Structural - 
Torsion 
Loads and Stresses, Structural - 

Transient Dynamic 
Loads, Buffeting and Gust - Tail 
Loads, Buffeting - Wings 
Loads - Fuselages, Nacelles, and 

Canopies 
Loads, Gust - Wings 
Loads, Landing 

Landing - Ground-Run 
Landing - Ground-Run, 
Land 
Loads, Landing - Ground-Run, 
Water 
Landing - Impact 
Landing - Impact, Land 
Landing - Impact, Water 
Maneuvering - Tail 
Maneuvering - Wings 
Rotating Wings 
Loads, Steady - Tail 
Loads, Steady - Wings 
Lubricants 
Lubrication, Chemistry 



M 



Loads, 
Loads, 



Loads, 
Loads, 
Loads, 
Loads, 
Loads, 
Loads 



Subject 

Heading 

Number 

(4. 3. 7) 

(4.3.7.3) 

(4.3.7.2) 

(4.3.7.6) 

(4. 3. 7. 7) 

(4.3.7.7.1) 

(4.3.7.5) 

(4. 3. 7. 1) 

(4.3.7.4) 

(4.3.7.7.2) 
(4.1.1.2.3) 
(4.1.1.1.4) 

(4.1.1.3) 

(4,1,1,1.3) 

(4. 1. 2) 

(4.1.2.2) 

(4.1.2.2.1) 

(4.1.2.2.2) 

(4.1.2.1) 

(4.1.2.1.1) 

(4.1.2.1.2) 

(4.1.1.2.2) 

(4.1.1.1.2) 

(4.1.1.4) 

(4.1.1.2.1) 

(4.1.1.1.1) 

(3. 8. 5) 

(3.8.1.2) 



Mach Number Effects - Complete 

Wings (1.2.2.6) 

Mach Number Effects - Propellers (1. 5. 2. 5) 
Mach Number Effects - Wing Sections (1. 2. 1. 8) 
Mass and Gyroscopic Problems (1. 8. 6) 

Materials (5) 

See also 
Materials - Operating Stresses 
and Conditions 
Materials - Properties 
Materials - Types 
Materials - Operating Stresses and 

Conditions (5. 3) 

See also 
Materials, Propulsion System - 
Operating Stresses 



Subject Heading Outline 

Materials - Properties 
Materials - Properties 
Materials - Properties 

Materials - Properties 
Materials - Properties 



■ Compression 

- Corrosion 
Resistance 

- Creep 

- Effects of 



Subject 

Heading 

Number 

(5.2) 
(5.2.2) 



(5. 
(5. 



2.8) 
2.3) 



Materials 
Materials 
Materials 
Materials 
Materials 



Nuclear Radiation 
Properties - Fatigue 



Properties 
Properties 
Properties 
Properties 



- Flexure 

- Plasticity 

- Shear 

- Stress- 
Rupture 

- Structure 

- Tension 



(5. 2. 10) 
(5.2.5) 
(5. 2. 7) 

(5.2.13) 
(5.2.6) 



(5.2.4) 

(5.2.9) 

(5.2.1) 

(5.2.11) 



(5.3.2) 
(5.1) 



Materials - Properties 
Materials - Properties 
Materials - Properties - Thermal 
Materials, Propulsion System - 

Operating Stresses 
Materials - Types 
See also 

Adhesives 

Alloys, Heat-Resisting 

Aluminum 

Ceramals 

Ceramics 

Plastics 

Protective Coatings 

Steels 

Meteorology 

See also 

Atmosphere 

Ice Formation 
Missiles 
See also 

Missiles - Components in Combination 

Missiles - Specific Types 
Missiles - Components in Combination (1. 7. 2. 1) 
See also 

Interference, Jet - Missiles 

Tail-Body Combinations - Missiles 

Wing-Body Combinations - Missiles 

Wing-Tail -Body Combinations - 
Missiles 
Missiles - Specific Types (1. 7. 2. 2) 



N 



(6) 



(1.7.2) 



Navigation 


(7.2) 


Noise 


(7.4) 


Nozzles 


(1.4.2.2) 


Nuclear-Energy Systems 


(3.1.10) 



Operating Problems 
See also 
Fire Hazards 
Ice Prevention and Removal 



(7) 



212 



Subject Heading Outline 



Subject 

Heading 

Number 



Navigation 

Noise 

Operating Problems - General 

Operating Problems, Physiological 

Piloting Techniques 

Safety 
Operating Problems - General (7. 10) 

Operating Problems, Physiological (7. 8) 



Piloting Techniques (7. 7) 

Pipes (1.4.2.3) 

Planing Surfaces, Hydrodynamic (2. 6) 

Plastics (5.1.6) 

Plates, Flat (4.3.3.1) 

Plates, Flat - Stiffened (4. 3. 3. 1. 2) 

Plates, Flat - Unstiffened (4. 3. 3. 1. 1) 

Plates, Structural (4.3.3) 

See also 

Plates, Flat 
Profiles - Complete Wings (1. 2. 2. 2. 1) 

Propeller and Jet Combinations - 

Airplanes (1.7. 1. 1.4) 

Propeller Operating Conditions (1.5.6) 

Propeller-Spinner-Cowl Combinations (1. 5. 7) 
Propeller Theory (1. 5. 1) 

Propellers (1. 5) 

See also 

Propeller Operating Conditions 

Propeller -Spinner -C owl Combinations 

Propeller Theory 

Propellers - Design Variables 

Propellers - Designated Types 

Slipstream - Propellers 
Propellers - Design Variables (1. 5. 2) 

See also 

Blade Sections - Propellers 

Interference of Bodies - Propellers 

Mach Number Effects - Propellers 

Propellers, Dual-Rotation 

Propellers - Pitch and Yaw 

Propellers - Solidity 
Propellers - Designated Types (1. 

Propellers, Dual-Rotation (1.5. 

Pitch and Yaw (1. 5. 

Solidity (1.5. 



Propellers 

Propellers 

Propulsion 
See also 
Accessories and Accessory Functions 
Booster Systems, Auxiliary 
Combustion and Combustors 
Compression and Compressors 
Engines - Control 
Engines - Cooling 
Friction and Lubrication 
Fuels 
Gases - Properties 



5.3) 
2.7) 
2.9) 
2.2) 
(3) 



Subject Heading Outline 

Heat Transfer 

Propulsion - Complete Systems 
Propulsion Systems - Vibration and 

Flutter 
Turbines 
Propulsion - 
See also 
Engines, 
Engines, 
Engines, 
Engines, 
Engines, 
Engines, 
Nuclear - 
Rotors, 



Subject 

Heading 

Number 



Complete Systems 

Pulse -Jet 

Ram -Jet 

Reciprocating 

Rocket 

Turbojet 

Turbo-Propeller 
Energy Systems 
Jet-Driven 



(3.1) 



Propulsion Systems - Vibration and 

Flutter 
Protective Coatings 
Protuberances - Bodies 
Pumps, Jet and Thrust Augmentors 



R 



Regenerators 
Research Equipment 
See also 
Research Equipment, Free-Flight 
Research Equipment, Materials 
Research Equipment, Propulsion 
Research Equipment, Structures 
Wind Tunnels 
Research Equipment and Techniques 
See also 
Research Equipment 
Research Technique 
Research Equipment, Free -Flight 
Research Equipment, Materials 
Research Equipment, Propulsion 
Research Equipment, Structures 
Research Technique 
Research Technique, Aerodynamic 
Research Technique - Corrections 
Research Technique, Hydrodynamic 
Research Technique - Loads and 
Construction 
Research Technique - Mathematics 
Research Technique - Operating 
Problems 
Research Technique, Propulsion 
Reynolds Number Effects - Complete 

Wings 
Reynolds Number Effects - Wing 

Sections 
Rotating-Wing Aircraft 
See also 
Autogiros 
Helicopters 
Rotors, Jet-Driven 



(3. 13) 

(5.1.9) 

(1.3.2.5) 

(1.4.4) 



(3.9.2.4) 
(9.1) 



(9) 



(9.1.2) 
(9.1.6) 
(9.1.4) 
(9.1.7) 
(9.2) 
(9. 2. 2) 
(9.2.1) 
(9.2.3) 

(9.2.4) 
(9. 2. 7) 

(9.2.6) 
(9.2.5) 

(1.2.2.5) 

(1.2.1.7) 
(1.7.3) 



(3.1.9) 



213 



Subject 

Heading 

Number 



(7.1) 
(7.1.1) 
(4. 3. 5) 



(1.5.4) 

2.2.3.2) 

(1.8.3) 

(1.8.1) 



(1.8) 



Subject Heading Outline 

S 

Safety 

Safety - Pilot-Escape Techniques 
Shells, Structural 
See also 

Boxes, Structural 

Cylinders 
Slipstream - Propellers 
Slots and Slats - Complete Wings (1 
Spinning 
Stability 
See also 

Stability, Dynamic 

Stability, Static 
Stability and Control 
See also 

Control 

Flying Qualities 

Mass and Gyroscopic Problems 

Spinning 

Stability 

Stabilization, Automatic 

Stalling 
Stability and Control, Hydrodynamic (2. 10) 

Stability, Directional - Static (1. 8. 1. 1. 3) 

Stability, Dynamic (1. 8. 1. 2) 

See also 

Damping Derivatives - Stability 

Stability, Lateral and Directional - 

Dynamic 

Stability, Longitudinal - Dynamic 
Stability, Lateral and Directional - 

Dynamic (1 
Stability, Lateral - Static (1 

Stability, Longitudinal - Dynamic (1 
Stability, Longitudinal - Static (1 

Stability, Static 
See also 

Stability, Directional - Static 

Stability, Lateral - Static 

Stability, Longitudinal - Static 
Stabilization, Automatic 
Stalling 

Standard Atmosphere 
Starting Systems 
Steels 
Structures 
See also 

Beams, Structural 

Columns, Structural 

Connections, Structural 

Loads and Stresses, Structural 

Plates, Structural 

Shells, Structural 

Weight Analysis 
Summaries, Technical (12) 

Surface Conditions - Complete Wings(l. 2. 2. 2. 6) 
Surface Conditions - Wing Sections (1. 2. 1. 2. 5) 



Subject Heading Outline 



.8.1.2.2) 
.8.1.1.2) 
.8.1.2.1) 
.8.1.1.1) 
(1.8.1.1) 



(1. 8. 8) 

(1.8.4) 

(6. 1. 1) 

(3. 12. 3) 

(5.1.3) 
(4.3) 



Surface Craft 
Surfaces, Contact 
See also 
Gears 



Sliding and Rolling 



Subject 
Heading 

Number 

(2.8) 
(3.8.4) 



1.3) 
7.2) 
7.1) 



(3.7) 



Tail-Body Combinations - Missiles (1. 7. 2. 1. 2) 
Tail-Wing-Fuselage Combinations - 

Airplanes (1. 7. 1 
Turbine Cooling (3 

Turbine Flow - Theory and Experiment (3 
See also 

Turbines - Axial-Flow 

Turbines - Mixed-Flow 
Turbines 
See also 

Turbine Cooling 

Turbine Flow - Theory and Experiment 

Turbines - Stress and Vibration 
Turbines - Axial-Flow (3. 7. 1. 1) 

Turbines, Gas - Afterburning (3. 3. 2. 2) 

Turbines, Gas - Bleedoff (3.3.2.3) 

Turbines, Gas - Liquid-Injection (3. 3. 2. 1) 

Turbines - Mixed-Flow (3. 7. 1. 3) 

Turbines - Stress and Vibration (3. 7. 3) 



(4.2.2.1) 
(4. 2. 6) 
(4.2.4) 



5) 
2) 



Vibration and Flutter (4. 2) 

Vibration and Flutter - Bodies (4.2. 3) 

Vibration and Flutter - Elevators and 

Rudders 

Vibration and Flutter - Panels and 

Surface Coverings 

Vibration and Flutter - Propellers, 

Fans, and Compressors 

Vibration and Flutter - Rotating - 

Wing Aircraft (4. 2 

Vibration and Flutter - Tails (4.2, 

See also 

Vibration and Flutter - Elevators 
and Rudders 
Vibration and Flutter - Wings and 

Ailerons (4. 2. 1) 



W 



Weight Analysis (4.3.8) 

Wind Tunnels (9. 1. 1) 
Wing-Body Combinations - Missiles (1. 7. 2. 1. 1) 
Wing- Fuselage Combinations - 

Airplanes (1. 7. 1. 1. 1) 
Wing-Nacelle Combinations - 

Airplanes (1. 7. 1. 1. 2) 

Wing Sections - Theory (1. 2. 1. 1) 



Wing Sections 
See also 
Boundary Layer 



(1.2.1) 



Wing Sections 



Subject Heading Outline 



Subject 

Heading 

Number 



Subject Heading Outline 



Subject 

Heading 

Number 



Controls - Wing Sections 
Mach Number Effects - Wing Sections 
Reynolds Number Effects - Wing 
Sections 
Wing Sections - Theory 
Wing Sections - Profiles, Designated 
Wing Sections - Section Variables 
Wing Sections - Wake 
Wing Sections - Camber (1. 2. 1. 2. 1) 

Wing Sections - Profiles, Designated (1. 2. 1. 3) 
Wing Sections - Section Variables (1.2.1.2) 

See also 
Surface Conditions - Wing Sections 
Wing Sections - Camber 
Wing Sections - Thickness 
Wing Sections - Thickness 
Distribution 
Wing Sections - Thickness (1. 2. 1. 2. 2) 

Wing Sections - Thickness 

Distribution (1.2. 1.2.3) 

Wing Sections - Wake (1. 2. 1. 9) 

Wing-Tail-Body Combinations - 

Missiles (1.7.2.1.4) 

Wings (1.2) 

See also 
Wing Sections 
Wings, Complete 
Wings, Complete (1.2.2) 

See also 
Boundary Layer - Complete Wings 
Controls - Complete Wings 
High-Lift Devices - Complete Wings 



Mach Number Effects - Complete 

Wings 
Reynolds Number Effects - Complete 

Wings 
Wings, Complete - Design Variables 
Wings, Complete - Theory 
Wings, Complete - Wake 
Wings, Complete - Aspect Ratio (1. 2. 2. 2. 2) 
Wings, Complete - Design Variables (1. 2. 2. 2) 
See also 
Dihedral - Complete Wings 
Inlets and Exits - Complete Wings 
Profiles - Complete Wings 
Surface Conditions - Complete Wings 
Wings, Complete - Aspect Ratio 
Wings, Complete - Sweep 
Wings, Complete - Taper and Twist 
Wings, Complete - Sweep (1. 2. 2. 2. 3) 

Wings, Complete - Taper and 

Twist (1.2.2.2.4) 

Wings, Complete - Theory (1. 2. 2. 1) 

Wings, Complete - Wake (1. 2. 2. 7) 

Wings, Rotating (1.6) 

See also 

Wings, Rotating - Experimental 

Studies 
Wings, Rotating - Theory 
Wings, Rotating - Experimental 

Studies (1.6.2) 

Wings, Rotating - Power-Driven (1. 6. 2. 1) 

Wings, Rotating - Theory (1. 6. 1) 



AUTHOR INDEX 




215 



Abraham, E. D., 172 
Abramson, H. Norman, 82(2) 
Ackerman, Arthur C, 27 
Adams, James J., 102(2) 
Agostini, Leon, 12 
Aiken, William S., Jr., 46, 155 
Alexander, Sidney R., 55 
Alford, William J., Jr., 21(2), 42 
Algranti, Joseph S., 18 
Alksne, Alberta Y., 2, 5, 46 
Allen, Edwin C, 23, 24 
Allen, Harry Julian, 9 
Allen, Hubert W., 4 
Allis, Arthur E., 65 
Altshuller, Aubrey P., 133 
Amer, Kenneth B., 68, 87(3) 
Amme, Robert C, 2 
Anderson, Melvin S., 166(2) 
Anderson, Roger A., 166(2) 
Anderson, SethB., 16, 30 
Anderson, Warren E., 57, 61 
Anton, Leo, 2 
Assadourian, Arthur, 36 
Axelson, John A., 5, 45 



B 



Bailey, John M., 146 
Baker, John E., 115 
Baker, Sol, 128 
Baldwin, Barrett S., Jr., 53 
Bandettini, Angelo, 22, 29(2) 
Banner, Richard D., 24 
Barling, Walter H., Jr., 21 
Barnett, Henry C, 132 
Bartlett, Walter A., Jr., 128 
Bartoo, Edward R., 144(2) 
Bass, J., 12 

Bates, William R., 27, 65, 66(2) 
Batterson, Sidney A., 119 
Baughman, L. Eugene, 13 
Beam, Benjamin H., 99 
Bear, H. Robert, 144 
Becht, Robert E., 16, 22 
Beede, William L., 141 
Beeler, De Elroy, 19 
Belles, Frank E M 132 
Bellman, Donald R., 28 
Benedict, William Sidney, 152 
Benthem, J. P., 166 
Beranek, Leo Leroy, 187 
Bernstein, Harry, 7 
Bertram, Mitchel H., 6, 9 
Bielat, Ralph P., 29 
Bingham, Gene J., 40 
Bisson, EdmondE., 127 
Black, DugaldO., 126, 128(2) 
Black, John Merle, 173 
Blackaby, James R., 58 
Blackshear, Perry L., 136 



Bland, William M., Jr., 17, 27, 38, 43 

Blivas, Darnold, 65 

Blokhintsev, D. I., 201 

Blomquist, Richard Frederick, 173 

Bloom, Martin, 166 

Boatright, William B., 33 

Bobbitt, Percy J., 8 

Boddy, Lee Elmer, 22, 25, 41 

Bogardus, K. O., 168 

Bogdan, Louis J., 126 

Bollecli, Thomas V., 30 

Boltz, Frederick W., 28, 30 

Bond, W. E., 172(2) 

Boswinkle, Robert W., Jr., 44, 57 

Boucher, Robert W., 100 

Bowden, Dean T., 17 

Bowman, James S., Jr., 112 

Boyd, George M., Jr., 117 

Boyd, John W., 20 

Braden, John A., 57 

Brajnikoff, George B., 56, 57 

Braslow, Albert Lewis, 40 

Bray, Richards., 29, 30(3), 71, 82 

Breitwieser, Roland, 129, 136 

Brevoort, Maurice John, 3, 7 

Briggs, Donald W., 28, 46 

Briggs, William B., 64 

Brikowski, Harold Joseph, 132 

Brinich, Paul F., Jr., 8, 9 

Bromm, August F., Jr., 9 

Brown, B. Porter, 105 

Brown, Clinton E., 25 

Brown, Stuart C, 82 

Brown, W. Byron, 14 

Brummer, Edmund A., 187 

Brun, Rinaldo J., 2, 17, 182(2) 

Brunk, William E., 7 

Bryan, Carroll R., 42, 56 

Buchele, Donald R., 4 

Budiansky, Bernard, 166 

Buell, Donald A., 35(2) 

Burbank, Paige B., 8 

Burgess, Marvin F., 65 

Burrows, Dale L., 40 

Busemann, Adolf, 3 

Butze, Helmut F., 134 

Byrd, Paul F., 9, 21 

Byrdsong, Thomas A., 116 

Byrnes, Andrew L., Jr., 16, 24, 32 



Cahill, Jones F., 20, 77 
Cahn, Maurices., 42 
Callaghan, Edmund E., 13(2) 
Calvert, Howard F., 126 
Campbell, George S., 21, 29 
Campbell, John P., 24 
Cancro, Patrick A., 36 
Canning, Thomas N., 47 
Carden, John R., 80 
Carlson, Edward R., 136 



216 



18 



126 



158(2) 



Carlton, William W., 128 

Carpenter, PaulJ., 87, 88 

Castles, Walter, Jr., 2 

Cervenka, AdolphJ., 128(2) 

Chapman, DeanR., 10, 17, 

Chauvin, Leo T., 5(2), 15 

Cheatham, Donald C, 99 

Chelko, Louis J., 126 

Childs, J. Howard, 138, 139 

Childs, Joan M., 44 

Chilton, Robert G., 180 

Christopher, Kenneth W., 118 

Chu, Boa-Teh, 14, 15 

Chwick, Alexander, 166 

Ciepluch, CarlC, 62 

Clauss, Francis J,, 127 

Cleary, Joseph W., 22(2) 

Clevenson, Sherman A., 4, 5, 164 

Clift, Dorothy C, 19 

Clure, John L., 144(3) 

Coats, James W., 62 

Cochran, Reeves P., 14, 

Cocke, Bennie W., 20 

Cohen, Clarence B., 11 

Cohen, Doris, 7 

Cohen, Robert J., 53 

Cole, J. A., 146 

Coleman, Thomas L., 157, 

Coles, WillardD., 13(3) 

Coletti, Donald E., 6 

Conner, D. William, 37 

Connors, James F., 8, 60(4) 

Cook, Francis E., 161 

Cook, William P., 131 

Cooper, Anthony L., 172 

Cooper, George E., 42, 82(2) 

Copp, Martin R., 157 

Cortright, Edgar M., Jr., 2 

Costilow, Eleanor L., 141(3) 

Crane, Harold L., 180 

Crawford, Robert F., 167(2) 

Crim, Aimer D., 88 

Croom, Delwin R., 39 

Cunningham, Herbert J., 8 

Curfman, Howard J., Jr., 41, 86, 100 

Czarnecki, Kazimierz Roman, 6, 10, 11 



Daley, Bernard N., 5 
Danforth, Edward C. B., 4 
Dangle, E. E., 128 
Dannenberg, Robert E., 19 
Davenport, William W., 163(2) 
Davids, Joseph, 58 
Davis, Don D., Jr., 7, 87, 158 
Davis, Wallace Frederick, 6(2), 57(2) 
Deich, M. E., 53 
Deissler, Robert G., 12 
De Leeuw, Jacob Henri, 2 
Demarkles, Louis R-, 168 
Demele, Fred A., 37, 75 



deMoraes, Carlos A., 15 

Dennard, John S., 199 

Dennis, David H., 8(2) 

Dettwyler, H. Rudolph, 128 

Deutsch, George C, 126, 173(2) 

Deveikis, William D., 166, 167 

Dewalt, W. J., 168 

Dewey, Paul E., 57 

DeYoung, John, 21 

Diaconis, NickS., 9 

Diaguila, Anthony J., 144, 145(2) 

Dick, RichardS., 5 

Dickey, Robert R., 53 

Dickson, Jerald K., 35, 66 

Diederich, Franklin Wolfgang, 24, 25 

Diederich, Margarets., 21 

Dietz, Albert E., 27, 72 

Disher, John H., 128 

Dittrich, Ralph T., 3 

Dods, Jules B., Jr., 24 

Donegan, James J., 101, 170 

Donely, Philip, 113 

Donnell, Lloyd Hamilton, 166 

Donoughe, Patrick L., 10, 11, 15 

Donov, A. E., 1 

Dorsch, Robert G., 83 

Dow, Norris F., 166 

Drake, Hubert M., 18, 41, 80(3) 

Draper, John W., 29 

Dreher, Robert C, 161 

Drischler, Joseph A., 25 

Duberg, John E., 166 

DuBois, George B., 146 

DuBose, Hugh C, 16 

Dunavant, James C, 63 

Dunn, Angel H., 23 

Dunning, Robert W., 18 



Eckert, Ernst Rudolf Georg , 14(2), 144, 

Edge, Philip M., Jr., 117 

Edwards, George G., 27, 35(2) 

Edwards, Sherman S., 57(2) 

Eggers, Alford J., Jr., 2, 8 

Eggleston, John M., 100 

ElBadrawy, RashadM., 9 

Embry, UrselR., 16 

Emerson, Horace F., 23 

Emery, James C, 63(4) 

Emmons, Howard W., 146 

English, Roland D., 29, 38 

Erickson, Burton 166(2) 

Ernstein, Norman E., 12 

Erwin, John R., 63(5) 

Esenwein, Fred T., 6 

Estabrooks, Bruce B., 26, 51 

Eubanks, A. G., 173 

Evans, David G., 144 

199 

, Jr., 128 

. 61 



145(3) 



Evans, John S., 
Evans, Philip J. 
Eward, John C. 



217 



Faget, MaximeA., 128(2) 

Faison, M. Frances, 16 

Falabella, Gaetano, Jr., 68 

Feiler, Charles E., 132(2), 135 

Felix, A. Richard, 63(2) 

Feller, William V., 7 

Ferri, Antonio, 57 

Fetner, Mary W., 158(2) 

Few, Albert G., Jr., 23 

Fields, Edison M., 20, 26, 37 

Finch, Thomas W., 28(2), 30 

Findley, William Nichols, 173 

Fine, Burton D., 10 

Fink, Marvin P., 20 

Fisher, Lewis R., 78 

Fisher, Newman H., Jr., 7 

Fitzpatrick, James E., 25, 34 

Fleming, Frank F., 26, 56 

Fortini, Anthony, 129 

Foster, Gerald V., 25, 26(2), 28(2), 33, 34 

Foster, Hampton Hoge, 126, 129 

Founder, Paul G., 23, 24, 69 

Fox, Jerome L., 59 

Fradenburgh, Evan A., 4 

Frank, Charles E., 137 

Franken, Peter A., 187 

Franks, Ralph W., 28(2) 

Friedman, Morris D., 7 

Friedman, Robert, 136 

Fuller, FranklynR., 20 

Fuller, Kenneth E,, 163 

Furlong, G. Chester, 30 



Gallagher, James J., 7 

Gambucci, Bruno J., 19 

Gammon, Benson E., 126, 128(4), 129 

Gardiner, Robert A., 83, 102 

Gardner, William N., 41 

Garrett, Floyd B., 127 

Garrick, Isadore Edward, 65 

Gates, Ordway B., Jr., 101 

Gault, Donald E., 11 

Germain, P., 2 

Ger stein, Melvin, 134 

Gessow, Alfred, 68(3) 

Giamati, Charles C, 64 

Gillespie, Warren, Jr., 72 

Gillis, Clarence L., 113 

Glasser, Philip W., 126 

Gloria, Hermilo R M 6 

Godwin, William R., 63 

Goin, KennithL., 33, 35, 37 

Goldstein, David L., 6(2) 

Gooderum, PaulB., 5 

Goodman, Alex, 30 

Goodman, Harold R., 41 

Goodson, Kenneth W., 39 

Goodwin, Julia M., 9 



Gordon, Sanford, 129 
Gowen, Forrest E., 9 
Gracey, William, 185, 194 
Graham, David, 24, 26, 27(2) 
Graham, Robert R., 28 
Graham, Robert W., 141 
Grala, Edward M., 172 
Grant, Frederick C., 8 
Graves, Charles C, 3, 134(2), 139 
Gray, Wilbur H., 66 
Greathouse, William K., 3(2) 
Griffith, George E., 14(3) 
Grigsby, CarlE., 7, 84, 86 
Griner, Roland F., 26(2), 33 
Grover, Horace John, 170, 172 
Gurnick, Raymonds., 172 
Gustafson, Frederic Bowen, 87(2) 



H 



Hacker, PaulT., 2, 186 
Haire, William M., 47 
Hakkinen, Raimo Jaakko, 3 
Hall, Albert W., 161 
Hallissy, Joseph M., Jr., 4, 66 
Hamer, Harold A., 80(2) 
Hammack, Jerome B., 4 
Hammond, Alexander D., 28, 29, 39 
Hample, W. G., 161 
Hamrick, Joseph T., 141 
Haney, Francis J., 187 
Hansen, Arthur G., 10, 64 
Hanson, Carl M., 20 
Harder, Keith C, 4, 8 
Hardrath, Herbert F., 170 
Harrin,-Eziaslav N., 161 
Harrison, William N., 173 
Hart, Roger G., 52, 53(2) 
Hauser, Cavour H., 63 
Havill, C. Dewey, 82, 83 
Heaslet, Maxwell Alford, 69 
Heath, Atwood R., Jr., 66(2) 
Hedgepeth, John M., 20, 116, 163 
Heimerl, George J., 172(2) 
Heinke, Harry S., Jr., 6, 25 
Heitkotter, Robert H., 177 
Heldenfels, Richard R., 14(2) 
Henderson, Campbell, 80 
Henderson, James H., 19, 30 
Henry, Beverly Z., Jr., 25, 26 
Henry, JohnR., 4 
Henzel, James G., Jr., 3 
Herr, Robert W., 31 
Herrig, L. Joseph, 63(2) 
Herrmann, George, 163 
Herzig, Howard Z., 10, 64 
Hess, Robert W., 169 
Heyson, Harry H., 2, 49 
Hibbard, Robert R., 133 
Higginbotham, James T., 4, 5 
Himmel, Seymour C, 65 
Hoff, Nicholas John, 166 



218 



Hoffman, Sherwood, 22, 26, 27(2), 70, 71(2), 72 

Holden, George R., 82 

Holdstock, N. G., 127 

Hollister, Donald P., 3(2) 

Holzhauser, Curt A., 28 

Hoover, Herbert H., 41 



21, 

55 



49 



170 



Hopkins, Edward J. 

Hopko, Russell N. 

Hord, Richard A., 8 

Home, Walter B., 162 

Houbolt, JohnC, 158, 162 

Howard, Darnley M., 172 

Howell, Francis McMurtrie, 

Howes, Walton L., 4 

Hubbard, Harvey H., 65, 169 

Huber, Paul W., 3 

Hubka, Ralph E., 166 

Huckel, Vera, 8 

Huff, VearlN., 129 

Huffman, Jarrett K., 39 

Humphrey, JackC, 129 

Humphreys, Milton D., 5 

Huntley, Sidney C, 58, 131 

Huppert, Merle Cecil, 126, 127, 141(3) 

Huss, CarlR., 80, 170 

Huston, WilberB., 46, 155 

Hyler, Walter S., 170, 172 



Ikard, Wallace L., 165 
Ingard, Uno, 187(2) 
Inge, JohnE., 172(2) 
Ingebo, Robert D., 129(2) 
Innis, Robert C, 30 
Irvine, Thomas F., Jr., 145 



Jack, John R., 9 
Jacques, William A., 27, 28 
Jacquet, Pierre A., 172 
James, Harry A., 20 
Jaquet, Byron M., 24, 29 
Johnson, AldieE., Jr., 167 
Johnson, Ben H., Jr., 22, 37, 76 
Johnson, Donald F., 141 
Johnson, Harold I., 5, 70 
Johnson, Harold S., 29, 37 
Johnson, Joseph L., Jr., 29 
Johnson, R. C, 3 
Johnson, Robert L., 127, 146(2) 
Johnston, J. Ford, 4 
Jones, Robert Thomas, 7, 8 
Jones, William L., 126 
Jorgensen, LelandH., 9, 10 
Judd, Joseph H., 128 

K 

Kaattari, George E., 23 
Kadow, Charles F., 83, 129 



Kapryan, Walter J., 117 

Karo, Wolf, 132 

Katz, Ellis R., 18, 52, 53 

Katzen, Elliott D., 23(2) 

Katzoff, Samuel, 2, 16 

Kaufman, Albert, 126, 183 

Kaufman, Samuel J., 129 

Keffer, Barbara M., 28, 29 

Kehlet, AlanB., 69 

Kell, Robert J., 20 

Kelly, Thomas C, 27 

Kempner, Joseph, 166 

Kennedy, Robert M., 28 

Kenyon, George C, 58, 59 

Kepert, J. L., 158 

Kester, Robert H., 17 

King, Thomas J., Jr., 32, 39, 43, 44 

Kinsler, Martin R., 14 

Kirby, Robert H., 56 

Kirkpatrick, Harry B., 173 

Kissel, M. A., 172(2) 

Klawans, Bernard B., 70 

Klebanoff, Philip Samuel, 4 

Klunker, E. Bernard, 4 

Knapp, Ronald J., 21 

Kochendorfer, FredD., 62 

Koenig, David G., 26, 27(2), 28(2) 

Koffel, William K., 149 

Kofskey, Milton G., 4 

Kohl, Robert C, 70 

Kolbe, CarlD., 30 

Kolnick, Joseph J., 28 

Kordes, EldonE., 158, 163(2) 

Kotanchik, Joseph N., 167 

Kovasznay, Leslies. G., 3 

Kowalski, Kenneth L., 13 

Kraft, Christopher C, Jr., 100, 111 

Kramer, James J., 2(2) 

Krasner, Morton H., 126 

Krebs, Richard P., 65, 87 

Kriebel, Anthony R., 63 

Krishnamurty, K., 4 

Krull, H. George, 62 

Krumm, Walter J., 23(2) 

Kruszewski, Edwin T., 163(3) 

Kuehn, Donald M., 10(2) 

Kuehnel, Helmut A., 101, 102 

Kuhn, Paul, 170 

Kuhn, Richard E., 23, 27, 29(2), 33(3), 69 

Kuhns, Perry W., 133 

Kurbjun, MaxC, 4(2), 51, 127 



Labate, Samuel, 187 

Lad, Robert A., 172 

Ladanyi, Dezso Joseph, 129(3), 132(2) 

Landers, Charles B., 170(2) 

Larson, Howard K., 10 

Lassiter, Leslie W., 169 

Laufer, John, 2 

Laurence, James C, 4, 15 



219 



Lauten, William T., Jr., 2, 27 

Lawrence, Leslie F., 37 

Lee, Edwin E., Jr., 88 

Legvold, Sam, 2 

Leiss, Abraham, 84 

Leonard, Robert W., 116 

Letko, William, 30 

Levine, Oscar, 134 

Lewis, William, 2, 182 

Libove, Charles, 166, 167 

Lichtenstein, Jacob H., 78 

Liebiein, Seymour, 20 

Lietzke, Armin F., 148 

Lin, T.C., 7 

Lina, Lindsay John, 33 

Lindsey, Walter Frank, 5 

Lipson, Stanley, 20 

Little, Barney Hugh, Jr., 4 

Livingood, John N. B., 10, 11, 14, 145 

Loeb, Julien, 111 

Loitsianskii, L. G., 2 

Lomax, Harvard, 20, 53, 69(2) 

Lopez, Armando E., 27, 34, 66 

Love, Eugene S., 3, 6(3), 8, 22 

Lovell, Powell M., Jr., 27, 65, 66(2), 99 

Loving, Donald L., 26, 155 

Low, Emmet F., Jr., 167(2) 

Lowell, Herman H., 148 

Lowry, John G., 5, 29 

Luidens, Roger W., 6 

Luoma, Arvo A., 17 



McArdle, Jack G., 3, 57, 62(2) 
McBride, Ellis E., 117 
McCafferty, Richard J., 132 
McCauley, William D., 7 
McCloud, John L., 3d., 20 
McComb, Harvey G., Jr., 167(2) 
McCormack, Gerald M., 26 
McCready, Robert R., 204 
McCullough, George Burns, 16, 27 
McDearmon, Russell W., 6 
McDevitt, John B., 3, 23, 47 
McDougal, Robert L., 158 
McFadden, Norman M., 20, 30, 71 
McFarland, Donald R., 3 
McGehee, John R., 117, 119, 120 
McKay, James M., 161 
McKay, John B., 18 
McKeown, Anderson B., 133 
McKinney, Marion O., Jr., 24, 100 
McKinnon, Roy A., 15 
McLaughlin, Milton D., 19 
McLellan, Charles Herbert, 6 
McMullan, Barbara M., 39 
McNeill, Walter E., 82 
Mace, William D., 187 
Maglieri, Domenic J., 68 
Maki, Ralph L., 16 
Male, Donald W., 128 



Maloney, Joseph P., 5, 7 

Malvestuto, Frank S., Jr., 7 

Manning. George King, 172 

Mantler, Raymond L., 136 

Mapp, Richard C, Jr., 71 

Marcy, William L., 24 

Maringer, Robert E., 172 

Markey, Melvin F., 117 

Marley, Edward T., 27, 38 

Marsh, L. L., 172 

Martin, Andrew, 23 

Martin, Dennis J., 23, 83 

Martin, James A., 16 

Martin, John C, 7 

Martin, Robert K., 28 

Martina, Albert P., 33 

Mason, Homer P., 44 

Massa, Rudolph V., 136 

Mastrocola, Nicholas, 36 

Mathauser, Eldon E., 166, 167 

Mathews, Charles W., 89, 100, 102(2) 

Matteson, Frederick H., 16, 45, 46 

Matthews, Clarence W., 202 

Matthews, James T\, Jr., 105 

Meadows, May T., 158 

Mecklenborg, Kenneth T., 146 

Mendeison, Alexander, 64 

Merlet, Charles F., 56(2) 

Messing, Wesley E., 128(3) 

Meyer, Andre J., Jr., 126(2), 173, 183 

Meyer, John R., Jr., 68 

Meyer, Rudolph C, 8 

Michael, William H., Jr., 8(2) 

Mickelsen, William R., 12(2) 

Miele, Angelo, 83(2) 

Milillo, Joseph R., 56 

Miller, Riley O., 129(2), 132(4), 135 

Miller, William S., Jr., 87 

Miitonberger, Georgene H., 14 

Milwitzky, Benjamin, 161 

Mirels, Harold, 11, 58 

Mitcham, Grady L., 41 

Mitchell, Meade H., Jr., 33, 37, 57 

Mobassery, Abol H., 166 

Moeckel, Wolfgang E., 3, 6, 9 

Molk, Ashley J., 59 

Mollenberg, Ernst F., 34 

Montgomery, Stephen R., 63 

Moore, Dewey, 87 

Moore, Dwight G., 173 

Moore, Franklin K., 3, 11 

Moore, John A., 6, 8 

Mordfin, Leonard, 168 

Morduchow, Morris, 4 

Morgan, William C, 126, 173(2) 

Morrell, Gerald, 129, 132, 135 

Morrill, Charles P., Jr., 22, 25, 41 

Morris, Garland J., 28, 29, 33 

Morrison, William D., Jr., 21 

Morrow, John D., 18(2), 54, 69, 70 

Moser, Jacob C, 126 

Moses, Jason J., 63 



220 



Mottard, Elmo J., 120 
Moul, Martin T., 87(2) 
Mueller, James N., 6, 7 
Muggia, Aldo, 1 
Mull, Harold R., 18 
Murray, S. F., 127 
Myers, P. S., 132 

N 

Nachtigall, Alfred J., 126 

Nelson, Herbert C, 2, 8 

Nelson, Robert L., 69 

Nelson, Warren Howard, 22, 23(3) 

Nelson, William J., 7 

Newman, Ernest E., 77 

Nichols, Mark R., 58 

Nielsen, Jack N., 23, 70 

Niewald, Roy J., 87 

Norris, Harry P., 41 

North, Warren J., 13, 62, 125 

Nothwang, George J., 9 

Novik, David, 127 

Nucci, Louis M., 57 

Nussdorfer, Theodore J., 12 



Obery, Leonard J., 6 
O'Bryan, Thomas C, 4 
Ocvirk, FredW., 146 
O'Donnell, Robert M., 6 
Ogburn, Edmund L., 7 
O'Keliy, Burke R., 27 
O'Neal, Robert L., 66 
Orchin, Milton, 133 
Ordin, Paul M., 129 
Osborn, Walter M., 141 
Osborne, Robert S., 26, 198 
Ostrach, Simon, 3(2), 10 



Pack, George J., 127 

Palmer, William E., 22 

Parker, Hermon M., 52 

Parkinson, John Bingham, 118 

Parks, James H., 69 

Parlett, Lysle P., 66, 99, 100 

Pasteur, Thomas B., Jr., 32, 43 

Patel, SharadA., 166(2) 

Patton, Norman A., 148 

Paulson, John W., 29 

Payne, A. O., 158 

Pearson, Merwin D., 197 

Peithman, Harlan W., 173 

Pendley, Robert E., 58 

Penland, Jim A., 7 

Pepper, William B., Jr., 22(3), 27(2), 70, 71 

Perchonok, Eugene, 128(3) 

Perkins, Edward W., 9(2), 10(2), 47 

Perkins, Porter J., Jr., 2, 182 

Petersen, R, E., 146 



Peterson, Marshall B., 146 

Phillips, William E., Jr., 127 

Phillips, William Hewitt, 31, 101, 102, 105 

Pierpont, P. Kenneth, 57 

Piland, Robert O., 9 

Pinkel, Benjamin, 173 

Pittel, Murray, 21 

Pitts, William C, 74 

Plohr, Henry W., 63 

Polhamus, Edward C, 3 

Povolny, John H., 57, 126 

Pratt, Kermit George, 158 

Predvoditelev, A. A., 174 

Press, Harry, 158 

Prian, Vasily D., 2, 141 

Pridmore-Brown, David C, 187 

Priem, R. J., 132 

Purser, Paul Emil, 19, 20, 32, 54, 96 

Putland, Leonard W., 54, 56 



Queijo, Manuel J., 25, 29 

R 

Racisz, Stanley Frank, 29 

Radin, Edward J., 87 

Rainey, A. Gerald, 25, 158, 164 

Rainey, Robert W., 33 

Rashis, Bernard, 3, 7 

Rathert, George A., Jr., 20, 30, 42, 71 

Rayle, Warren D., 136 

Reed, Robert D., 24, 74 

Reed, Verlin D., 34 

Reed, Wiimer H., 3d., 48 

Reeder, John Paul, 88(2) 

Reese, David E., Jr., 99 

Reese, James R., 163 

Regier, Arthur A., 23 

Reisert, Thomas D. f 68 

Rennemann, Conrad, Jr., 8 

Reshotko, Eli, 11, 62 

Resnikoff, Meyer M., 8 

Rey, William K., 175 

Reynolds, Robert M., 58, 59(3), 65 

Reynolds, Thaine W., 129(2) 

Rhines, Frederick N., 172(2) 

Ribner, Herbert Spencer, 7 

Richards, Hadley T., 14 

Richmond, Joseph C, 173 

Riebe, John M., 34 

Riley, Donald R., 45 

Robinson, Samuel W., Jr., 101 

Rogers, Arthur William, 56 

Rogers, John T., 23 

Rollins, Francis W., 76 

Rolls, L. Stewart, 20, 60, 82, 83 

Rosecrans, Richard J., 14(2) 

Rosen, B. Waiter, 167 

Roshko, Anatol, 4(2) 

Ross, Robert D., 167 

Rossing, Thomas D., 2 



221 



Roudebush, William H., 20 
Rousso, Morris D., 13, 62 
Rowe, J, R., 64 
Ruggeri, Robert S., 13 
Runckel, Jack F., 19 
Runyan, Harry L., 116, 164 
Russell, Walter R., 194 
Rutishauser, Heinz, 204 



Saari, Martin John, 59 

Sabol, Alexander P., 199 

Sacks, Alvin H., 21, 49 

Sadoff, Melvin, 46 

Salmi, Reino J., 26, 27 

Salters, L eland B., Jr., 66 

Saltzman, Edwin J., 17 

Sammonds, Robert I., 58 

Sandahl, Carl A., 16, 17, 36, 37(3), 107 

Sandborn, Virgil A., 15 

Sanders, E. Claude, Jr., 21(2) 

Sanders, J. Lyell, Jr., 166 

Sanders, Newell Drake, 149 

Saper, Paul G., 83, 129 

Savage, Melvyn, 63 

Savin, Raymond C, 2 

Sawyer, Richard H., 161 

Scallion, William L, 36 

Scheithauer, Elwood F., 4 

Scher, Stanley H., 112(2) 

Scherrer, Richard, 61 

Schlichting, Hermann, 11 

Schneider, Harold, 129 

Schneider, William C, 20 

Schnitzer, Emanuel, 117 

Schramm, Wilson B., 126 

Schrode, H., 162 

Schroeder, Albert H., 2, 60(4) 

Schubauer, Galen Brandt, 4 

Schueller, Carl F., 6 

Schult, Eugene D., 26, 37, 69 

Schy, Albert A., 101 

Seaberg, Ernest C, 99 

Sears, Richard I., 56(2) 

Seiff, Alvin, 199 

Selan, Ralph, 29(2), 39 

Sellers, Thomas B., 7 

Semonian, Joseph W., 166 

Serafini, John S., 2 

Serovy, George Kaspar, 63 

Shames, Harold, 65 

Sherman, Frederick S., "7 

Shibata, Harry H., 22(2), 28 

Shivers, James P., 88 

Shufflebarger, Charles C, 39 

Shuford, Charles L., 117 

Sibulkin, Merwin, 58 

Silsby, Norman S., 28, 29, 161 

Silvers, H. Norman, 42, 43, 44 

Simon, Paul C, 6, 13 

Sinclair, Archibald R., 10, 11 

Sines, George H., 175 



Sivells, James C, 37 

Skinner, George Tolmie, 195 

Skoog, Richard B = , 91 

Skopinski, T. H., 46, 155 

Sleeman, William C, Jr., 32 

Sione, Henry O., 14 

Sloop, John L., 129 

Sluder, Loma E., 20 

Smiley, Robert F., 162(3) 

Smirnov, B. A., 174 

Smith, Charles C, Jr., 27, 65, 66(2) 

Smith, Donald W., 34 

Smith, Frank C, 172 

Smith, G. Allan, 82 

Smith, Ira, 172 

Smith, Lawrence A., 21 

Smith, Philip L., 158 

Sonne, W., 102 

Sorensen, Norman E., 21, 49 

Sparrow, Ephraim M., 11, 129 

Spooner, Stanley H., 33(2) 

Spreemann, Kenneth P., 21, 33, 42(2) 

Spreiter, John R., 5(2), 20, 21 

Stamper, Eugene, 149 

Stead, Dexter H., 20 

Steffen, Fred W., 57, 62(3) 

Stein, Manuel, 166 

Stenning, Alan H., 63 

Stephenson, Bertrand H., 162 

Stephenson, Jack D., 39 

Stepka, Francis S., 126, 144 

Sterbentz, William H., 4, 58, 61(2), 128 

Stevens, George L., Jr., 87 

Stevens, Joseph E., 41 

Stewart, Warner L., 142, 144 

Stickney, Truman M., 3 

Stine, Howard A., 10 

Stokes, George M., 7, 87 

Stone, David Gregory, ^1(2), 37 

Stoney, William E., Jr., 52(2), 54 

Strass, H. Kurt, 17, 20, 26, 27, 31, 37(3), 107 

Street, Robert E., 7 

Stroud, John F., 57 

Summers, James L., 37 

Sutton, Fred B., 23, 75 

Swarts, Donald E., 133, 137 

Swett, Clyde C, Jr., 138 

Swihart, John M., 65(2) 

Swikert, Max A., 146 

Sylvester, Maurice A., 65, 115 

Syvertson, Clarence A., 6, 8 



Tang, Kenneth K., 23 
Tapscott, Robert J., 68(2), 87(4), 88 
Thomas, David F., Jr., 25, 30, 33 
Thompson, Jim Rogers, 4(2), 82 
Thompson, Robert F., 30, 31 
Timing, Bruce E., 24, 27(2), 34, 76 
Tischler, Adelbert O., 136 
Tobak, Murray, 99(2) 
Tolefson, Harold B., 158 



222 



Tomassoni, John E., 4 
Tower, Leonard K., 126, 136 
Triplett, William C, 82 
Trout, Otto F., Jr., 128 
Tsien, V. C, 166 
Tucker, Warren A., 20 
Tuovila, Weimer J., 6(2) 
Turner, Thomas R., 29, 30 

U 

Ulmann, Edward F., 18 
Useller, James W., 126 
Uyehara, O. A., 132 



Valentine, E. Floyd, 5 

Van Dyke, Milton Denman, 7(2) 

Van Dyke, Rudolph D., Jr., 16, 45, 46, 98 

Vick, Allen R., 7, 57 

Videan, Edward N., 82 

Vidensek, Robert J., 166 

Vincent, K. R., 58 

Vincenti, Waiter G., 5, 7 

Vladimirov, A. N., 117 

Vogler, Raymond D., 39 

Vogt, Dorothea E., 17 

Vosteen, Louis F., 163 

W 

Wadlin, Kenneth L., 117, 119 
Wagner, Paul, 10(2) 
Wakil, M. M. El, 132 
Walker, John H., 65 
Walker, Joseph A., 28 
Walker, Walter G., 158(2) 
Wall, Helen L, 80 
Wallner, Lewis E., 59 
Walls, James H., 162 
Wallskog, Harvey A., 69 
Ward, Vernon G. , 197(2) 
Watkins, Charles E., 65 
Watson, Earl C, 57 
Watson, Raymonds., 128 
Wear, Jerrold D., 126 
Weeton, John Waldemar, 127 
Wehe, R. L., 146 
Weiberg, James A., 19, 27 
Weick, Fred Ernest, 82(2) 
Weil, Joseph, 21, 32 
Weinflash, Bernard, 120 



Welsh, Clement J., 17, 54, 70 
Weltmann, Ruth N., 133 
Westphal, Willard R., 63 
Whitcomb, Charles F., 197, 198 
Whitcomb, Richard Travis, 27, 44 
White, Maurice Donald, 22 
Whitten, James B., 88, 102 
Widmayer, Edward, Jr., 5 
Wiener, Bernard, 46 
Wiggins, James W., 23, 27, 29, 69 
Wilbur, Stafford W., 4(2) 
Wilcox, Fred A., 61, 128(3) 
Wiley, Harleth G., 45 
Wilken, Gertrude V., 21 
Williams, James L., 24, 30, 54 
Williams, Katherine D., 78 
Wilsted, H. Dean, 58 
Wimbrow, William R., 16 
Windier, Milton L., 4 
Wineman, Andrew R., 87 
Winograd, Lee, 98 
Winovich, Warren, 10 
Wishnek, George, 128 
Withee, Joseph R., Jr., 141 
Wolhart, Walter D., 25, 29, 30 
Wollett, Richard R., 61 
Wong, Edgar L., 134 
Wood, Charles C, 4, 5 
Wood, George P., 5, 9 
Wood, Raymond B., 26, 69 
Woodling, Carroll H., 101 
Woods, Robert L., 33, 34(2) 
Woolley, Harold W., 152(2) 
Woolston, Donald S., 116, 164 
Worley, Will J., 173 
Wright, Ray H., 197 
Wu, Chung-Hua, 2 
Wyatt, DeMarquis D., 4 
Wyss, John A., 19 



Yacobi, Laura A., 63 
Yates, Edward Carson, Jr., 8, 10 
Yntema, Robert T., 87 
Yoshimura, Yoshimaru, 167 



Zarovsky, Jacob, 83, 102 
Zender, George W., 166, 167 
Zettie, Eugene V., 131 
Ziff, Howard L., 42 
Zlotnick, Martin, 24, 25 



NACA - Langley Field, Va.