Index of NACA technical publications

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Title:
Index of NACA technical publications
Physical Description:
9 v. : ; 26 cm.
Language:
English
Creator:
United States -- National Advisory Committee for Aeronautics
United States -- National Aeronautics and Space Administration
Publisher:
NACA
Place of Publication:
Washington
Frequency:
irregular

Subjects

Subjects / Keywords:
Aeronautics -- Abstracts   ( lcsh )
Genre:
serial   ( sobekcm )
abstract or summary   ( marcgt )
federal government publication   ( marcgt )

Notes

Dates or Sequential Designation:
Began with: 1915-1947.
Dates or Sequential Designation:
-July 1957-Sept. 1958.
Numbering Peculiarities:
Cumulation for 1915-1947 superseded by 1915-1949, which is supplemented by subsequent volumes.
Issuing Body:
Vol. for July 1957-Sept. 1958 issued by: National Aeronautics and Space Administration.
General Note:
Description based on: 1915-1949; title from cover.
Statement of Responsibility:
National Advisory Committee for Aeronautics.

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Source Institution:
University of Florida
Rights Management:
All applicable rights reserved by the source institution and holding location.
Resource Identifier:
aleph - 030392191
oclc - 01775947
lccn - 48045822 //r822
Classification:
lcc - Z5063 .U634
System ID:
AA00022327:00002

Related Items

Succeeded by:
Index of NASA technical publications

Full Text



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PREFACE



The Preface to the Index of NACA Technical Publications,
1915-1949, mentioned that regular supplements would be issued
in the future. This is the first such Supplement and covers those
documents issued through May of 1951. Similar arrangement is
used in both Indexes. First, there is a classified listing of the
subject categories; second, a chronological listing of NACA pub-
lications under each subject category; third, an alphabetical index
to the subject categories; and finally, an author index. The latter
feature was not included in the basic 1915-1949 Index but has been
issued separately and is available upon request. Immediately fol-
lowing this Preface is an Explanatory Chart of NACA Publications
Series Designations which may be of use in identifying references
to NACA documents encountered in the literature.

For those maintaining a file of NACA index cards, it is
recommended that cards issued for reports dated prior to June 1,
1951, be removed from the file as this volume includes the same
index information.

NACA documents issued since June 1, 1951, have been
listed in NACA Research Abstracts, a new announcement service
which also includes notices of declassification of NACA docu-
ments and listings of unpublished NACA documents available on
loan.





Division of Research Information
National Advisory Committee for Aeronautics
1724 F Street, N. W.
Washington 25, D. C.



April 23, 1952



















Digitized by the Internet Archive
in 2014













http://archive.org/details/indexofnac 1951 unit








EXPLANATORY CHART OF NACA PUBLICATIONS SERIES
DESIGNATIONS


NUMBER
NUMBER BASED ON
NUMBERED BASED ON DATE OF ISSUE-
CURRENTLY CONSECU- LABORATORY** YEAR* MONTH#
PUBLICATIONS SERIES SYMBOL ISSUED TIVELY OF ORIGIN DAY### EXAMPLE WITH EXPLANATION

Reports None Yes Yes No No Report 1004 1004th Report issued.
Research Memorandums RM Yes No Yes Yes RM L9K03a Research Memorandum written by Langley
Laboratory Personnel in 1949 and issued on November 3rd,
being the second RM released on that date.
Technical Memorandums TM Yes Yes No No TM 1313 1313th Technical Memorandum issued.
Technical Notes TN Yes Yes No No TN 2432 2432nd Technical Note issued.
Wartime Reports WR No Yes Yes No WR A-6 6th Wartime Report issued that was based on
Ames Laboratory research. Reported earlier to a
limited audience and was reprinted.
Adv. Conf. Reports ACR No No Yes, after Yes, after ACR E4D19 Advance Confidential Report written by
March, 1944## April, 1943## Lewis Laboratory personnel in 1944 and issued on April 19th.
Adv. Rest'd Reports ARR No No Yes, after Yes, after ARR L4K22b Advance Restricted Report written by
March, 1944## April, 1943## Langley Laboratory personnel in 1944 and issued on
November 22nd, being the 3rd ARR issued on that date.
Conf. Bulletins CB No No Yes, after Yes, after CB E5J11 Confidential Bulletin written by Lewis
March, 1944## April, 1943## Laboratory personnel in 1945 and issued October llth.
Memorandum Reports MR No No Yes, after Yes, after MR A4L12 Memorandum Report written by Ames Labo-
October, 1944## October, 1944## ratory personnel in 1944 and issued on December 12th.
Restricted Bulletins RB No No Yes, after Yes, after RB L5F15 Restricted Bulletin written by Lewis Labo-
March, 1944## April, 1943## ratory personnel in 1945 and issued on June 15th.
Aircraft Circulars AC No Yes No No AC 150 150th Aircraft Circular issued.

## Symbol and date only ** A Ames 5 1945 50 1950 A January G July ### 01
used prior to date E Lewis 6 1946 51 1951 B February H August 02
mentioned. L Langley 7 1947 52 1952 C March I September 03 .etc. to 31 followed by
8 1948 D April J October a 2nd document issued that date
9 1949 E May K November b 3rd document issued that date
F June L December





CONTENTS

Subject Subject
No. Subject Page No. Subject Page

1 AERODYNAMICS 1 1.3.1 Theory 44
1.3.2 Shape Variables 44
1.1 Fundamental Aerodynamics 2 1.3.2.1 Fineness Ratio 44
1.1.1 Incompressible Flow 2 1.3.2.3 Thickness Distribution 45
1.1.2 Compressible Flow 3 1.3.2.4 Surface Conditions 45
1.1.2.1 Subsonic Flow 4 1.3.3 Canopies 45
1.1.2.2 Mixed Flow 6 1.3.4 Ducted Bodies 45
1.1.2.3 Supersonic Flow 7 1.3.4.1 Nose Shape 45
1.1.3 Viscous Flow 10 1.4 Internal Aerodynamics 46
1.1.3.1 Laminar Flow 10 1.4.1 Air Inlets 46
1.1.3.2 Turbulent Flow 12 1.4.1.1 Nose, Central 46
1.1.3.3 Jet Mixing 13 1.4.1.1.2 Subsonic 46
1.1.4 Aerodynamics with Heat 14 1.4.1.1.3 Supersonic 46
1.1.4.1 Heating 15 1.4.1.2 Nose, Annular 46
1.1.4.2 Heat Transfer 15 1.4.1.3 Wing Leading Edge 47
1.1.4.3 Additions of Heat 16 1.4.1.4 Side 47
1.1.5 Flow of Rarefied Gases 17 1.4.1.4.1 Scoops 47
1.1.5.2 Free Molecule Flow 17 1.4.2 Ducts 47
1.4.2.1 Diffusers 47
1.2 Wings 18 1.4.2.1.1 Subsonic 47
1.2.1 Wing Sections 18 1.4.2.1.2 Supersonic 47
1.2.1.1 Section Theory 18 1.4.2.2 Nozzles 47
1.2.1.2 Section Variables 19 1.4.2.3 Pipes 48
1.2.1.2.1 Camber 19 1.4.2.4 Bends 48
1.2.1.2.2 Thickness 19 1.4.3 Exits 48
1.2.1.2.3 Thickness Distribution 20 1.4.5 Cascades 48
1.2.1.2.4 Inlets and Exits 21 1.4.5.1 Theory 49
1.2.1.2.5 Surface Conditions 21 1.4.5.2 Experiment 49
1.2.1.3 Designated Profiles 21 1.4.6 Fans 49
1.2.1.4 High Lift Devices 21 1.4.7 Boundary Layer 50
1.2.1.4.1 Plain Flaps 21 1.4.7.1 Characteristics 50
1.2.1.4.2 Split Flaps 22 1.4.7.2 Control 51
1.2.1.4.3 Slotted Flaps 22 1.5 Propellers 52
1.2.1.4.4 Leading Edge Flaps 22 1.5.1 Theory 52
1.2.1.5 Controls 22 1.5.2 Design Variables 52
1.2.1.5.1 Flap Type 22 1.5.2.1 Blade Sections 52
1.2.1.6 Boundary Layer 23 1.5.2.2 Solidity 53
1.2.1.6.1 Characteristics 23 1.5.2.3 Pitch Distribution 53
1.2.1.6.2 Control 24 1.5.2.4 Blade Planforms 53
1.2.1.7 Reynolds Number 1.5.2.5 Mach Number Effects 53
Effects 24 1.5.2.6 Pusher 54
1.2.1.8 Mach Number Effects 24 1.5.2.7 Dual Rotation 54
1.2.2 Complete Wings 25 1.5.2.8 Interference of Bodies 54
1.2.2.1 Wing Theory 25 1.5.2.9 Pitch and Yaw 54
1.2.2.2 Wing Variables 29 1.5.2.10 Diameter 54
1.2.2.2.1 Profiles 29 1.5.3 Designated Types 54
1.2.2.2.2 Aspect Ratio 29 1.5.4 Slipstream 55
1.2.2.2.3 Sweep 31 1.5.6 Operating Conditions 55
1.2.2.2.4 Taper and Twist 34 1.6 Rotating Wings 56
1.2.2.2.6 Surface Conditions 35 1.6.1 Theory 56
1.2.2.2.7 Dihedral 36 1.6.2 Experimental Studies 56
1.2.2.3 High Lift Devices 36 1.6.2.1 Power-Driven 56
1.2.2.3.1 Trailing Edge Flaps 36 1.6.2.2 Autorotating 57
1.2.2.3.2 Slots and Slats 37 1.7 Aircraft 58
1.2.2.4 Controls 37 1.7.1 Airplanes 58
1J2.2.4.1 Flap Type 37 1.7.1.1 Components in
1.2.2.4.2 Spoilers 39 Combination 58
1.2.2.5 Reynolds Number Effects 39 1.7. 1. 1.1 Wing-Fuselage 58
1.2.2.6 Mach Number Effects 39 1.7.1.1.2 Wing-Nacelle 58
1.2.2.7 Wake 42 1.7. 1.3 Tail-Wing and Fuselage 59
1.2.2.8 Boundary Layer 42 1.7.1.1.5 External Stores 59
1.3 Bodies 44 1.7.1.2 Specific Airplanes 59

iv





Subject Subject
No. Subject Page No. Subject Page

1.7.1.3 Performance 60 3.1.2.2 Compound Engines 92
1.7.2 Missiles 60 3.1.2.3 Gas Generator-Turbine
1.7.2.1 Components in Engines 92
Combination 61 3.1.3 Turbo-Jet Engines 92
1.7.2. 1. 1 Wing-Body 61 3.1.4 Turbo-Propeller Engines 94
1.7.2.1.2 Tail-Body 61 3.1.5 Ducted Propeller Engines 94
1.7.2.1.3 Jet Interference 61 3.1.6 Pulse Jet Engines 94
1.7.2.2 Specific Missiles 61 3.1.7 Ram Jet Engines 94
1.7.3 Rotating Wing Aircraft 61 3.1.8 Rocket Engines 95
1.7.3.1 Autogiros 61 3.1.9 Jet-Driven Rotors 95
1.7.3.2 Helicopters 61 3.1.12 Comparison of Engine Types 95
1.8 Stability and Control 63 3.2 Control of Engines 96
1.8.1.1.1 Longitudinal 63 3.2.1 Charging and Control of
1.8.1.1.2 Lateral 65 Reciprocating Engines 96
1.8.1.1.3 Directional 65 3.2.1.3 Compound Engines 96
1.8.1.2 Dynamic 66 3.2.2 Control of Turbojet Engines 96
1.8.1.2.1 Longitudinal 66 3.2.3 Control of Turbine-Ramjet
1.8.1.2.2 Lateral and Directional 67 Engines 97
1.8.1.2.3 Damping Derivatives 69 3.2.4 Control of Turbine-
1.8.2 Control 71 Propeller Engines 97
1.8.2.1 Longitudinal 71 3.2.5 Control of Pulse-Jet Engines 97
1.8.2.2 Lateral 72 3.2.6 Control of Ramjet Engines 97
1.8.2.3 Directional 73 3.2.8 Control of Gas Generator
1.8.2.4 Airbrakes 73 Engines 97
1.8.2.5 Hinge Moments 73 3.3 Auxiliary Booster Systems 98
1.8.2.6 Automatic 74 3.3.2.1 Liquid Injection 98
1.8.3 Spinning 75 3.3.2.2 Afterburning 98
1.8.4 Stalling 75 3.3.2.3 Bleed-off 98a
1.8.5 Flying Qualities 76 3.4 Fuels 99
1.8.6 Mass and Gyroscopic 3.4.1 Preparation 99
Problems 77 3.4.2 Physical and Chemical
1.8.8 Automatic Stabilization 77 Properties 99
1.9 Aeroelasticity 79 3.4.3 Relation to Engine
1.10 Parachutes 80 Performance 100
3.4.3.1 Reciprocating Engines 100
2 HYDRODYNAMICS 81 3.4.3. 1 1 Spark-Ignition 100
3.4.3.2 Turbine Engines, Ram
2.1 Theory 81 Jets, and Pulse Jets 101
2.2 General Arrangement Studies 82 3.4.3.3 Rockets (Includes Fuel
2.3 Seaplane Hull Variables 83 and Oxidant) 101
2.3.1 Length-Beam Ratio 83 3.5 Combustion and Combustors 102
2.3.2 Deadrise 83 3.5.1 General Combustion
2.3.3 Steps 83 Research 102
2.3.4 Afterbody Shape 84 3.5.1.1 Laminar-Flow
2.3.5 Forebody Shape 84 Combustion 102
2.3.6 Chines 84 3.5.1.2 Turbulent-Flow
2.4 Specific Seaplanes and Hulls 85 Combustion 103
2.6 Planing Surfaces 86 3.5.1.3 Detonation 103
2.7 Hydrofoils 87 3.5.1.4 Effects of Fuel Atomiza-
2.8 Surface Craft 88 tion 103
2.9 Ditching Characteristics 89 3.5.1.5 Reaction Mechanisms 103
2.10 Stability and Control 90 3.5.1.6 Ignition of Gases 103
2.10.1 Longitudinal 90 3.5.2 Effect of Engine Operating
2.10.3 Directional 90 Conditions and Combus-
tion Chamber Geometry 103
3 PROPULSION 91 3.5.2.1.1 Spark-Ignition Engines 104
3.5.2.2 Turbine Engines 104
3.1 Complete Systems 91 3.5.2.3 Ram-Jet Engines 104
3.1.1 Reciprocating Engines 91 3.6 Compression and Compressors 105
3.1.1 1 Spark-Ignition Engines 91 3.6.1 Flow Theory and Experi-
3. 1 1.2 Compression-Ignition ment 105
(Diesel) Engines 91 3.6.1.1 Axial Flow 105
3.1,2 Reciprocating Engines 3.6.1.2 Radial Flow 106
Turbines 91 3.6.1.3 Mixed Flow 107

V





Subject Subject
No. Subject Page No. Subject Page

3.6.1.4 Positive Displacement 107 4.2 Vibration and Flutter 127
3.6.2 Stress and Vibration 107 4.2.1 Wings and Ailerons 127
3.6.3 Matching 108 4.2.3 Bodies 128
3.7 Turbines 109 4.2.4 Propeller, Fans, and
3.7.1 Flow Theory and Experi- Compressors 128
ment 109 4.2.5 Rotating Wing Aircraft 128
3.7.1.1 Axial Flow 109 4.3 Structures 129
3.7.1.2 Radial Flow 110 4.3.1 Columns 129
3.7.1.3 Mixed Flow 110 4.3.1.2 Beams 129
3.7.2 Cooling 110 4.3.1.3 Sections 129
3.7.3 Stress and Vibration 110 4.3.3 Plates 129
3.7.4 Matching 111 4.3.3.1 Flat 129
3.8 Friction and Lubrication 113 4.3.3.1.1 Unstiffened 129
3.8.1 Theory and Experiment 113 4.3.3.1.2 Stiffened 130
3.8.1.1 Hydrodynamic Theory 113 4.3.3.2 Curved 130
3.8.1.2 Chemistry of Lubri- 4.3.3.2.1 Unstiffened 130
cation 113 4.3.3.2.2 Stiffened 130
3.8.1.3 Surface Conditions 114 4.3.4 Beams 130
3.8.2 Sliding Contact Surfaces 114 4.3.4.1 Box 131
3.8.3 Rolling Contact Surfaces 114 4.3.4.2 Diagonal Tension 131
3.8.3.1 Anti-Friction Bearings 114 4.3.5 Shells 131
3.8.4 Sliding and Rolling Contact 4.3.5.1.1 Circular 131
Surfaces 115 4.3.5.1.2 Elliptical 132
3.8.5 Lubricants 115 4.3.6 Connections 132
3.9 Heat Transfer 116 4.3.6.1 Bolted 132
3.9.1 Theory and Experiment 116 4.3.6.2 Riveted 132
3.9.1.1 Cascades 117 4.3.6.3 Welded 132
3.9.2 Heat Exchangers 117 4.3.7 Loads and Stresses 132
3.9.2.4 Regenerators 117 4.3.7.1 Tension 132
3.10 Cooling of Engines 118 4.3.7.2 Compression 132
3.10.1 Reciprocating Engines 118 4.3.7.3 Bending 133
3.10.1.1 Liquid Cooled 118 4.3.7.4 Torsion 134
3.10.2 Gas Turbine Systems 118 4.3.7.5 Shear 134
3.10..3 Ram Jets 118 4.3.7.6 Concentrated 134
3.11 Properties of Gases 119 4.3.7.7 Dynamic 134
3.11.1 Kinetic 119 4.3.7.7.1 Repeated 135
3.11.2 Thermodynamic 119 4.3.7.7.2 Transi ent 135
3.12 Accessories and Accessory 4.3.7.8 Normal Pressures 135
Functions 120
3.12.1 Fuel Systems 120 5 MATERIALS 138
3.12.1.4 Turbojet Engines 120
3.12.1.5 Turbine-Propeller Engines 120 5.1 Types 138
3.12.1.8 Rocket Engines 120 5.1.1 Aluminum 138
3.12.4 Lubrication Systems 120 5.1.2 Magnesium 139
5.1.3 Steels 139
4 AIRCRAFT LOADS AND 5.1.4 Heat-Resisting Alloys 139
CONSTRUCTION 121 5.1.5 Ceramics 140
5.1.6 Plastics 140
4.1 Loads 121 5.1.7 Woods 141
4.1.1 Aerodynamic 121 5.1.8 Adhesives 141
4.1. 1.1 Wings 121 5.1.9 Protective Coatings 141
4. .1.I.1 Steady Loads 122 5.1.10 Fabrics 141
4.1.1.1.2 Maneuvering 122 5.1.11 Sandwich and Laminates 141
4.1.1.1.3 Gust Loads 123 5.1.12 Ceramals 142
4.1.1.2 Tail 124 5.2 Properties 143
4.1.1.2.1 Steady Loads 124 5.2.1 Tensile 143
4.1.1.2.2 Maneuvering 124 5.2.2 Compressive 144
4.1.1.2.3 Buffeting and Gust 124 5.2.3 Creep 144
4.1.1.3 Fuselage, Nacelles, 5.2.4 Stress-Rupture 144
and Canopies 124 5.2.5 Fatigue 144
4.1.1.4 Rotating Wings 125 5.2.6 Shear 145
4.1.1.5 Aeroelasticity 125 5.2.7 Flexural 145
4.1.2.1 Impact 125 5.2.8 Corrosion Resistance 145
4.1.2.1.2 Water 125 5.2.9 Structure 145

vi







Subject
No. Subject Page

5.2.10 Effects of Nuclear Radiation 146
5.2.11 Thermal 146
5.2.12 Multi-Axial Stress 146
5.2.13 Plasticity 146
5.3 Operating Stresses and
Conditions 148
5.3.1 Airframe 148

6 METEOROLOGY 151

6.1 Atmosphere 151
6.1.2 Gusts 151
6.1.2.1 Structure 151
6.1.2.2 Frequency 151
6.1.2.3 Turbulence 151
6.1.2.4 Alleviation 151
6.2 Ice Formation 153

7 OPERATING PROBLEMS 156

7.1 Safety 156
7.2 Navigation 157
7.3 Ice Prevention and Removal 158
7.3.1 Engine Induction Systems 158
7.3.2 Propellers 158
7.3.3 Wings and Tails 158
7.3.5 Miscellaneous Accessories 158
7.3.6 Propulsion Systems 158
7.4 Noise 159
7.5 Heating and Ventilating 160
7.7 Piloting Techniques 161
7.9 Fire Hazards 162

8 INSTRUMENTS 163

8.1 Flight 165
8.2 Laboratory 166
8.3 Meteorological 167

9 RESEARCH EQUIPMENT AND
TECHNIQUES 169

9.1 Equipment 171
9.1.1 Wind Tunnels 171
9.1.2 Free-Flight 172
9.1.3 Towing Tanks and Impact
Basins 172
9.1.4 Propulsion Research
Equipment 172
9.1.6 Materials 173
9.2 Technique 174
9.2.1 Corrections 174
9.2.2 Aerodynamics 175
9.2.4 Loads and Construction 175
9.2.6 Operating Problems 175
9.2.7 Mathematics 176

11 BIBLIOGRAPHIES AND INDEXES 177

12 TECHNICAL SUMMARIES 179
vii















AERODYNAMICS
(1)








2 AERODYNAMICS





Fundamental

(1.1)


Heaslet, Max. A. and Lomax, Harvard: Jones, Robert T.: The Spanwise Distri-
The Use of Source-Sink and Doublet bution of Lift for Minimum Induced
Distributions Extended to the Solu- Drag of Wings Having a Given Lift
tion of Arbitrary Boundary Value and a Given Bending Moment.
Problems in Supersonic Flow. TN 2249, December 1950.
Rept. 900, 1948.
Van Dyke, Milton D.: A Study of Second-
Eggers, A. J., Jr.: One-Dimensional Order Supersonic-Flow Theory.
Flows of an Imperfect Diatomic Gas. TN 2200, January 1951.
Rept. 959, 1950.

Heaslet, Max. A. and Lomax, Harvard: INCOMPRESSIBLE FLOW
The Application of Green's Theorem
to the Solution of Boundary-Value 11.1
Problems in Linearized Supersonic
Wing Theory. Rept. 961, 1950. Katzoff, S.; Finn, Robert S.; and
Laurence, James C.: Interference
Brown, Clinton E.: The Reversibility Method for Obtaining the Potential
Theorem for Thin Airfoils in Sub- Flow past an Arbitrary Cascade of
sonic and Supersonic Flow. Rept. Airfoils. Rept. 879, 1947.
986, 1950.
Quick, August Wilhelm and Schrider, K.:
Allen, H. Julian: Pressure Distribution Behavior of the Laminar Boundary
and Some Effects of Viscosity on Layer for Periodically Oscillating
Slender Inclined Bodies of Revolu- Pressure Variation. TM 1228,
tion. TN 2044, March 1950. September 1949.

Neihouse, Anshal I. and Pepoon, Sanders, John C. and Brightwell,
Philip W.: Dynamic Similitude be- Virginia L.: Analysis of Ejector
tween a Model and a Full-Scale Thrust by Integration of Calculated
Body for Model Investigation at Surface Pressures. TN 1958,
Full-Scale Mach Number. TN 2062, October 1949.
March 1950.
Westphal, Willard R. and Dunavant,
Sanger, Eugen: The Gas Kinetics of Very James C.: Application of the Wire-
High Flight Speeds. TM 1270, May Mesh Plotting Device to Incompres-
1950. sible Cascade Flows. TN 2095,
May 1950.
Perl, William: Calculation of Transonic
Flows past Thin Airfoils by an Inte- Hansen, Arthur G. and Yohner, Peggy L.:
gral Method. TN 2130, July 1950. A Numerical Procedure for Design-
ing Cascade Blades with Prescribed
Martin, John C.: The Calculation of Velocity Distribution in Incompres-
Downwash behind Wings of Arbitrary sible Flow. TN 2101, June 1950.
Plan Forms at Supersonic Speeds.
TN 2135, July 1950. Barmby, J. G.; Cunningham, H. J.; and
Garrick, I. E.: Study of Effects of
Sweep on the Flutter of Cantilever
Wings. TN 2121, June 1950.







AERODYNAMICS
FUNDAMENTAL (1.1) 3

COMPRESSIBLE FLOW Spreiter, John R.: The Aerodynamic
Forces on Slender Plane- and
( 2) Cruciform-Wing and Body Combi-
nations. Rept. 962, 1950.
Lees, Lester: The Stability of the Lami-
nar Boundary Layer in a Compres- Tucker, Maurice: Approximate Turbu-
sible Fluid. Rept. 876, 1947. lent Boundary-Layer Development
in Plane Compressible Flow along
Spurr, Robert A. and Allen, H. Julian: Thermally Insulated Surfaces with
A Theory of Unstaggered Airfoil Application to Supersonic-Tunnel
Cascades in Compressible Flow. Contour Correction. TN 2045,
Rept. 888, 1947. March 1950.

Liepmann, Hans W. and Fila, Gertrude H.: Sibulkin, Merwin and Koffel,
Investigations of Effects of Surface William K.: Chart for Simplifying
Temperature and Single Roughness Calculation of Pressure Drop of a
Elements on Boundary-Layer Tran- High-Speed Compressible Fluid
sition. Rept. 890, 1947. under Simultaneous Action of
Friction and Heat Transfer Ap-
Matthews, Clarence W.: A Comparison plication to Combustion-Chamber
of the Experimental Subsonic Pres- Cooling Passages. TN 2067,
sure Distributions about Several March 1950.
Bodies of Revolution with Pressure
Distributions Computed by Means Frankl, F. I.: On the Formation of
of the Linearized Theory. RM Shock Waves in Subsonic Flows
L9F28, September 1949. with Local Supersonic Velocities.
TM 1251, April 1950.
Callaghan, Edmund E. and Bowden,
Dean T.: Investigation of Flow Co- Kiebel, I. A.: Some Studies on the Flow
efficient of Circular, Square, and of a Gas in the Region of Transition
Elliptical Orifices at High Pres- through the Velocity of Sound.
sure Ratios. TN 1947, September TM 1252, April 1950.
1949.
Kiebel, I. A.: Exact Solutions of Equa-
Sanders, John C. and Brightwell, tions of Gas Dynamics. TM 1260,
Virginia L. : Analysis of Ejector June 1950.
Thrust by Integration of Calculated
Surface Pressures. TN 1958, Soule, Harold V. and Sabol, Alexander P.:
October 1949. Development and Preliminary Inves-
tigation of a Method of Obtaining
Schafer, Manfred and Tollmien, W.: Hypersonic Aerodynamic Data by
Two-Dimensional Potential Flows. Firing Models through Highly
TM 1243, November 1949. Cooled Gases. TN 2120, July 1950.

Schafer, Manfred and Tollmien, W.: Perl, William: Calculation of Transonic
Rotationally Symmetric Potential Flows past Thin Airfoils by an Inte-
Flows. TM 1244, November 1949. gral Method. TN 2130, July 1950.

Heaslet, Max. A.; Lomax, Harvard; Kaplan, Carl: On the Particular Inte-
and Spreiter, John R.: Linearized grals of the Prandtl-Busemann
Compressible-Flow Theory for Iteration Equations for the Flow
Sonic Flight Speeds. Rept. 956, of a Compressible Fluid. TN
1950. 2159, August 1950.

Chapman, Dean R.: Laminar Mixing of Hamrick, Joseph T.; Ginsburg,
a Compressible Fluid. Rept. 958, Ambrose; and Osborn, Walter M.:
1950. Method of Analysis for Compres-
sible Flow through Mixed-Flow
Heaslet, Max. A. and Lomax, Harvard: Centrifugal Impellers of Arbitrary
The Application of Green's Theorem Design. TN 2165, August 1950.
to the Solution of Boundary-Value
Problems in Linearized Supersonic
Wing Theory. Rept. 961, 1950.








AERODYNAMICS
4 FUNDAMENTAL (1.1)

Compressible Flow (Cont.) Tucker, Maurice: Approximate Calcu-
lation of Turbulent Boundary-Layer
Pinkel, Benjamin; Noyes, Robert N.; Development in Compressible Flow.
and Valerino, Michael F.: Method TN 2337, April 1951.
for Determining Pressure Drop of
Air Flowing through Constant-Area Valerino, M. F. and Doyle, R. B.:
Passages for Arbitrary Heat-Input Method for Determining Pressure
Distributions. TN 2186, Septem- Drop of Monatomic Gases Flowing
ber 1950. in Turbulent Motion through Constant-
Area Passages with Simultaneous
Spooner, Robert B.: Effect of Heat- Friction and Heat Addition. TN
Capacity Lag on a Variety of 2328, April 1951.
Turbine-Nozzle Flow Processes.
TN 2193, October 1950. Karpovich, E. A. and Frankl, F. I.:
Resistance of a Delta Wing in a Su-
Ivey, H. Reese and Cline, Charles W.: personic Flow. TM 1283, April
Effect of Heat-Capacity Lag on the 1951.
Flow through Oblique Shock Waves.
TN 2196, October 1950. Bugaenko, G. A.: On the Problem of
Gas Flow over an Infinite Cascade
Lieblein, Seymour and Sandercock, Using Chaplygin's Approximation.
Donald M.: Compressibility Cor- TM 1298, May 1951.
rection for Turning Angles of Axial-
Flow Inlet Guide Vanes. TN 2215, Kuo, Yung-Huai: Two-Dimensional
December 1950. Transonic Flow past Airfoils. TN
2356, May 1951.
Stalder, Jackson R.; Goodwin, Glen;
and Creager, Marcus O.: A Com- Shu, S. S.: On Two-Dimensional Flow
parison of Theory and Experiment after a Curved Stationary Shock
for High-Speed Free-Molecule Flow. (with Special Reference to the Prob-
TN 2244, December 1950. lem of Detached Shock Waves). TN
2364, May 1951.
Lomax, Harvard; Heaslet, Max. A.; and
Fuller, Franklyn B.: Three- Sinnette, John T., Jr. and Costello,
Dimensional, Unsteady-Lift Prob- George R.: Possible Application of
lems in High-Speed Flight Basic Blade Boundary-Layer Control to
Concepts. TN 2256, December Improvement of Design and Off-
1950. Design Performance of Axial-Flow
Turbomachines. TN 2371, May
Wang, Chi-Teh: Two-Dimensional Sub- 1951.
sonic Compressible Flows past
Arbitrary Bodies by the Variational SUBSONIC FLOVW
Method. TN 2326, March 1951. (1.1.2.1)

Tucker, Maurice and Maslen, Stephen H.: Kaplan, Carl: On Similarity Rules for
Turbulent Boundary-Layer Tempera- Transonic Flows. Rept. 894, 1948.
ture Recovery Factors in Two-
Dimensional Supersonic Flow. TN Sinnette, John T., Jr.: Some Methods
2296, February 1951. of Analyzing the Effect of Basic
Design Variables on Axial-Flow
Moore, Franklin K.: Three-Dimensional Compressor Performance. Rept.
Compressible Laminar Boundary- 901, 1948.
Layer Flow. TN 2279, March 1951.
Jones, Robert T.: Subsonic Flow over
Liepmann, H. W.; Roshko, A.; and Thin Oblique Airfoils at Zero Lift.
Dhawan, S.: On Reflection of Shock Rept. 902, 1948.
Waves from Boundary Layers.
TN 2334, April 1951.







AERODYNAMICS
FUNDAMENTAL (1.1) 5
Subsonic Flow Compressible (Cont.)

Matthews, Clarence W.: A Comparison DeYoung, John: Theoretical Antisymmet-
of the Experimental Subsonic Pres- ric Span Loading for Wings of Arbi-
sure Distributions about Several trary Plan Form at Subsonic Speeds.
Bodies of Revolution with Pressure TN 2140, July 1950.
Distributions Computed by Means
of the Linearized Theory. RM Christianovich, S. A. and Yuriev, I. M.:
L9F28, September 1949. Subsonic Gas Flow past a Wing Pro-
file. TM 1250, July 1950.
Costello, George R.: Method of Design-
ing Cascade Blades with Prescribed Kaplan, Carl: On the Particular Integrals
Velocity Distributions in Compres- of the Prandtl-Busemann Iteration
sible Potential Flows. Rept. 978, Equations for the Flow of a Compres-
1950. sible Fluid. TN 2159, August 1950.

Herriot, John G.: Blockage Corrections Amick, James L.: Comparison of the
for Three-Dimensional-Flow Closed- Experimental Pressure Distribution
Throat Wind Tunnels, with Consid- on an NACA 0012 Profile at High
eration of the Effect of Compressi- Speeds with That Calculated by the
bility. Rept. 995, 1950. Relaxation Method. TN 2174,
August 1950.
Reissner, Eric: On the Theory of Oscil-
lating Airfoils of Finite Span in Sub- Lindsey, Walter F. and Chew, William L.:
sonic Compressible Flow. Rept. The Development and Performance
1002, 1950. of Two Small Tunnels Capable of
Intermittent Operation at Mach Num-
Bers, Lipman: Velocity Distribution on bers between 0.4 and 4. 0. TN 2189,
Wing Sections of Arbitrary Shape in September 1950.
Compressible Potential Flow. III -
Circulatory Flows Obeying the Furlong, G. Chester and Fitzpatrick,
Simplified Density-Speed Relation. James E.: Effects of Mach Number
TN 2056, March 1950. up to 0. 34 and Reynolds Number up
to 8 x 106 on the Maximum Lift Co-
Gelbart, Abe and Resch, Daniel: A efficient of a Wing of NACA 66-
Method of Computing Subsonic Flows Series Airfoil Sections. TN 2251,
around Given Airfoils. TN 2057, December 1950.
March 1950.
Harder, Keith C. and Klunker, E. B.:
Sibulkin, Merwin and Koffel, William K.: On a Source-Sink Method for the
Chart for Simplifying Calculation of Solution of the Prandtl-Busemann
Pressure Drop of a High-Speed Iteration Equations in Two-
Compressible Fluid under Simul- Dimensional Compressible Flow.
taneous Action of Friction and Heat TN 2253, December 1950.
Transfer Application to Combustion-
Chamber Cooling Passages. TN DeYoung, John: Theoretical Symmetric
2067, March 1950. Span Loading Due to Flap Deflec-
tion for Wings of Arbitrary Plan
Loewner, Charles: A Transformation Form at Subsonic Speeds. TN 2278,
Theory of the Partial Differential January 1951.
Equations of Gas Dynamics. TN
2065, April 1950. Reissner, Eric: Extension of the Theory
of Oscillating Airfoils of Finite Span
Roy, Maurice: Theoretical Investigations in Subsonic Compressible Flow.
on the Efficiency and the Conditions TN 2274, February 1951.
for the Realization of Jet Engines.
TM 1259, June 1950. Costello, George R.; Cummings,
Robert L.; and Sinnette, John T., Jr.:
Perl, William: Calculation of Transonic Detailed Computational Procedure for
Flows past Thin Airfoils by an Inte- Design of Cascade Blades with Pre-
gral Method. TN 2130, July 1950. scribed Velocity Distributions in
Compressible Potential Flows.
TN 2281, February 1951.







AERODYNAMICS
6 FUNDAMENTAL (1.1)

Subsonic Flow Compressible (Cont.) Matthews, Clarence W.: A Comparison
of the Experimental Subsonic Pres-
Harmon, Sidney M.: Correspondence sure Distributions about Several
Flows for Wings in Linearized Bodies of Revolution with Pressure
Potential Fields at Subsonic and Distributions Computed by Means of
Supersonic Speeds. TN 2303, the Linearized Theory. RM L9F28,
March 1951. September 1949.

Harmon, Sidney M.: Method for Cal- Heberle, Juergen W.; Wood, George P.;
culating Downwash Field Due to and Gooderum, Paul B.: Data on
Lifting Surfaces at Subsonic and Shape and Location of Detached
Supersonic Speeds. TN 2344, Shock Waves on Cones and Spheres.
April 1951. TN 2000, January 1950.

Klunker, E. B. and Harder, Keith C.: Frankl, F. I.: On the Formation of
On the Second-Order Tunnel-Wall- Shock Waves in Subsonic Flows with
Constriction Corrections in Two- Local Supersonic Velocities. TM
Dimensional Compressible Flow. 1251, April 1950.
TN 2350, April 1951.
Kiebel, I. A.: Some Studies on the Flow
Reissner, Eric: On the Application of of a Gas in the Region of Transition
Mathieu Functions in the Theory of through the Velocity of Sound. TM
Subsonic Compressible Flow past 1252, April 1950.
Oscillating Airfoils. TN 2363,
May 1951. Bers, Lipman: On the Continuation of a
Potential Gas Flow across the Sonic
Kaplan, Carl: On a Solution of the Non- Line. TN 2058, April 1950.
linear Differential Equation for
Transonic Flow past a Wave-Shaped Loewner, Charles: A Transformation
Wall. TN 2383, June 1951. Theory of the Partial Differential
Equations of Gas Dynamics. TN
MIXED FLOW 2065, April 1950.
(1.1.2.2)
Kiebel, I. A.: Exact Solutions of Equa-
Orlin, W. James; Lindner, Norman J.; tions of Gas Dynamics. TM 1260,
and Bitterly, Jack G. : Application June 1950.
of the Analogy between Water Flow
with a Free Surface and Two- Perl, William: Calculation of Transonic
Dimensional Compressible Gas Flows past Thin Airfoils by an
Flow. Rept. 875, 1947. Integral Method. TN 2130, July
1950.
Kaplan, Carl: On Similarity Rules for
Transonic Flows. Rept. 894, 1948. Gooderum, Paul B. and Wood, George P.:
Density Fields around a Sphere at
Zalovcik, John A. and Luke, Ernest P.: Mach Numbers 1.30 and 1.62. TN
Some Flight Measurements of 2173, August 1950.
Pressure-Distribution and Boundary-
Layer Characteristics in the Pres- Amick, James L.: Comparison of the
ence of Shock. RM L8C22, July Experimental Pressure Distribution
1948. on an NACA 0012 Profile at High
Speeds with that Calculated by the
Stack, John and Lindsey, W. F.: Char- Relaxation Method. TN 2174,
acteristics of Low-Aspect-Ratio August 1950.
Wings at Supercritical Mach Num-
bers. Rept. 922, 1949. Perl, W. and Klein, Milton M.: Theo-
retical Verification and Application
of Transonic Similarity Law for
Two-Dimensional Flow. TN 2191,
October 1950.








AERODYNAMICS
FUNDAMENTAL (1.1) 7

Mixed Flow Compressible (Cont.) Heaslet, Max. A.; Lomax, Harvard; and
Jones, Arthur L.: Volterra's Solu-
Cohen, C. B. and Valerino, A. S.: In- tion of the Wave Equation as Applied
vestigation of Operating Pressure to Three-Dimensional Supersonic
Ratio of a Supersonic Wind Tunnel Airfoil Problems. Rept. 889, 1947.
Utilizing Distributed Boundary-
Layer Suction in Test Section. Chapman, Dean R. and Perkins,
RM E50H04, November 1950. Edward W.: Experimental Investi-
gation of the Effects of Viscosity on
Szablewski, W.: The Diffusion of a Hot the Drag of Bodies of Revolution at
Air Jet in Air in Motion. TM 1288, a Mach Number of 1. 5. RM A7A31a,
December 1950. April 1947.

Perl, W. and Klein, Milton M.: Theo- Heaslet, Max. A. and Lomax, Harvard:
retical Investigation of Transonic The Use of Source-Sink and Doublet
Similarity for Bodies of Revolution. Distributions Extended to the Solu-
TN 2239, December 1950. tion of Arbitrary Boundary Value
Problems in Supersonic Flow.
Klein, Milton M. and Perl, W.: Cal- Rept. 900, 1948.
culation of Compressible Potential
Flow past Slender Bodies of Revolu- Pinkel, I. Irving: Equations for the De-
tion by an Integral Method. TN sign of Two-Dimensional Supersonic
2245, December 1950. Nozzles. Rept. 907, 1948.

Spreiter, John R.: Similarity Laws for Ribner, Herbert S. and Malvestuto,
Transonic Flow about Wings of Frank S., Jr.: Stability Derivatives
Finite Span. TN 2273, January 1951. of Triangular Wings at Supersonic
Speeds. Rept. 908, 1948.
Liepmann, H. W.; Roshko, A.; and
Dhawan, S.: On Reflection of Shock Ritter, William K. and Johnsen, Irving A.:
Waves from Boundary Layers. TN Performance of 24-Inch Supersonic
2334, April 1951. Axial-Flow Compressor in Air. I -
Performance of Compressor Rotor
Vincenti, Walter G. and Wagoner, Cleo B.: at Design Tip Speed of 1600 Feet
Transonic Flow past a Wedge Profile per Second. RM E7L10, May 1948.
with Detached Bow Wave General
Analytical Method and Final Calcu- Czarnecki, K. R. and Schueller, C. F.:
lated Results. TN 2339, April 1951. Investigation of Interaction Effects
Arising from Side-Wall Boundary
Shu, S. S.: On Two-Dimensional Flow Layers in Supersonic Wind-Tunnel
after a Curved Stationary Shock (with Tests of Airfoils. RM L8G27,
Special Reference to the Problem of November 1948.
Detached Shock Waves). TN 2364,
May 1951. Heaslet, Max. A. and Lomax, Harvard:
Two-Dimensional Unsteady Lift
Kaplan, Carl: On a Solution of the Non- Problems in Supersonic Flight.
linear Differential Equation for Rept. 945, 1949.
Transonic Flow past a Wave-Shaped
Wall. TN 2383, June 1951. Tollmien, W.: Theory of Characteristics.
TM 1242, September 1949
SUPERSONIC FLOW
(1. 1.2.3) Harmon, Sidney M.: Theoretical Rela-
tions between the Stability Deriva-
Garrick, I. E. and Rubinow, S. I.: tives of a Wing in Direct and in Re-
Theoretical Study of Air Forces on verse Supersonic Flow. TN 1943,
an Oscillating or Steady Thin Wing September 1949.
in a Supersonic Main Stream. Rept.
872, 1947.






AERODYNAMICS
8 FUNDAMENTAL (1.1)

Supersonic Flow Compressible (Cont.) Huckel, Vera and Durling, Barbara J.:
Tables of Wing-Aileron Coefficients
Falkovich, S. V.: Two-Dimensional of Oscillating Air Forces for Two-
Motion of a Gas at Large Super- Dimensional Supersonic Flow. TN
sonic Velocities. TM 1239, 2055, March 1950.
October 1949.
Haskind, M. D. and Falkovich, S. V.:
Gurevich, M. I.: Lift Force of an Vibration of a Wing of Finite Span
Arrow-Shaped Wing. TM 1245, in a Supersonic Flow. TM 1257,
October 1949. April 1950. 0

Schlifer, Manfred and Tollmien, W.: Bidwell, Jerold M.: Analysis of an In-
Two-Dimensional Potential Flows. duction Blowdown Supersonic Tunnel.
TM 1243, November 1949. TN 2040, April 1950.

Schifer, Manfred and Tollmien, W.: Loewner, Charles: A Transformation
Rotationally Symmetric Potential Theory of the Partial Differential
Flows. TM 1244, November 1949. Equations of Gas Dynamics. TN
2065, April 1950.
Evvard, John C.: Use of Source Dis-
tributions for Evaluating Theoreti- Harmon, Sidney M. and Jeffreys,
cal Aerodynamics of Thin Finite Isabella: Theoretical Lift and Damp-
Wings at Supersonic Speeds. ing in Roll of Thin Wings with Arbi-
Rept. 951, 1950. trary Sweep and Taper at Super-
sonic Speeds. Supersonic Leading
Gooderum, Paul B.; Wood, George P.; and Trailing Edges. TN 2114,
and Brevoort, Maurice J.: Investi- May 1950.
gation with an Interferometer of the
Turbulent Mixing of a Free Super- Vincenti, Walter G.: Comparison be-
sonic Jet. Rept. 963, 1950. tween Theory and Experiment for
Wings at Supersonic Speeds. TN
Kantrowitz, Arthur: The Supersonic 2100, June 1950.
Axial-Flow Compressor. Rept. 974,
1950. Jack, John R.: Theoretical Wave Drags
and Pressure Distributions for
Mirels, Harold and Haefeli, Rudolph C.: Axially Symmetric Open-Nose
Line-Vortex Theory for Calculation Bodies. TN 2115, June 1950.
of Supersonic Downwash. Rept. 983,
1950. Moore, Franklin: Linearized Supersonic
Axially Symmetric Flow about Open-
Lagerstrom, P. A.: Linearized Super- Nosed Bodies Obtained by Use of
sonic Theory of Conical Wings. Stream Function. TN 2116, June
TN 1685, January 1950. 1950.

Heberle, Juergen W.; Wood, George P.; Noyes, Robert N.: Prandtl-Meyer Flow
and Gooderum, Paul B.: Data on for a Diatomic Gas of Variable
Shape and Location of Detached Shock Specific Heat. TN 2125, June 1950.
Waves on Cones and Spheres. TN
2000, January 1950. Martin, John C.: The Calculation of
Downwash behind Wings of Arbitrary
Moskowitz, Barry and Moeckel, W. E.: Plan Form at Supersonic Speeds.
First-Order Theory for Unsteady TN 2135, July 1950.
Motion of Thin Wings at Supersonic
Speeds. TN 2034, February 1950. Chapman, Dean R.: An Analysis of Base
Pressure at Supersonic Velocities
Ribner, Herbert S.: Time-Dependent and Comparison with Experiment.
Downwash at the Tail and the Pitch- TN 2137, July 1950.
ing Moment Due to Normal Accel-
eration at Supersonic Speeds. TN
2042, February 1950.








AERODYNAMICS
FUNDAMENTAL (1.1) 9

Supersonic Flow Compressible (Cont.) Ferri, Antonio: Supersonic Flow around
Circular Cones at Angles of Attack.
Haefeli, Rudolph C.; Mirels, Harold; TN 2236, November 1950.
and Cummings, John L.: Charts
for Estimating Downwash behind Stalder, Jackson R.; Goodwin, Glen; and
Rectangular, Trapezoidal, and Creager, Marcus 0.: A Comparison
Triangular Wings at Supersonic of Theory and Experiment for High-
Speeds. TN 2141, August 1950. Speed Free-Molecule Flow. TN
2244, December 1950.
Mirels, Harold: Lift-Cancellation
Technique in Linearized Supersonic Ehret, Dorris M.; Rossow, Vernon J.;
Wing Theory. TN 2145, August and Stevens, Victor I.: An Analysis
1950. of the Applicability of the Hypersonic
Similarity Law to the Study of Flow
Ribner, Herbert S.: On the Effect of about Bodies of Revolution at Zero
Subsonic Trailing Edges on Damping Angle of Attack. TN 2250, Decem-
in Roll and Pitch of Thin Sweptback ber 1950.
Wings in a Supersonic Stream.
TN 2146, August 1950. Van Dyke, Milton D.: A Study of Second-
Order Supersonic-Flow Theory.
Ribner, Herbert S.: Some Conical and TN 2200, January 1951.
Quasi-Conical Flows in Linearized
Supersonic-Wing Theory. TN 2147, Lampert, Seymour: Rolling and Yawing
August 1950. Moments for Swept-Back Wings in
Sideslip at Supersonic Speeds.
Kaplan, Carl: On the Particular Inte- TN 2262, January 1951.
grals of the Prandtl-Busemann
Iteration Equations for the Flow Ribner, Herbert S.: Damping in Roll of
of a Compressible Fluid. TN 2159, Cruciform and Some Related Delta
August 1950. Wings at Supersonic Speeds. TN
2285, February 1951.
Gooderum, Paul B. and Wood, George P.:
Density Fields around a Sphere at Rubesin, Morris W.; Maydew, Randall C.;
Mach Numbers 1.30 and 1.62. and Varga, Steven A.: An Analyti-
TN 2173, August 1950. cal and Experimental Investigation
of the Skin Friction of the Turbulent
Lindsey, Walter F. and Chew, William L.: Boundary Layer on a Flat Plate at
The Development and Performance of Supersonic Speeds. TN 2305,
Two Small Tunnels Capable of Inter- February 1951.
mittent Operation at Mach Numbers
between 0.4 and 4.0. TN 2189, Cooper, Morton and Webster, Robert A.:
September 1950. The Use of an Uncalibrated Cone for
Determination of Flow Angles and
Brinich, Paul F.: Boundary-Layer Mach Numbers at Supersonic Speeds.
Measurements in 3.84- by 10-Inch TN 2190, March 1951.
Supersonic Channel. TN 2203,
October 1950. Harmon, Sidney M.: Correspondence
Flows for Wings in Linearized
Kainer, Julian H. and Marte, Jack E.: Potential Fields at Subsonic and
Theoretical Supersonic Character- Supersonic Speeds. TN 2303,
istics of Inboard Trailing-Edge Flaps March 1951.
Having Arbitrary Sweep and Taper.
Mach Lines behind Flap Leading and Chang, Chieh-Chien: Applications of
Trailing Edges. TN 2205, October Von Karman's Integral Method in
1950. Supersonic Wing Theory. TN 2317,
March 1951.
Pinkel, I. Irving and Serafini, John S.:
Graphical Method for Obtaining Flow Liepmann, H. W.; Roshko, A.; and
Field in a Two-Dimensional Super- Dhawan, S.: On Reflection of Shock
sonic Stream to which Heat Is Added. Waves from Boundary Layers.
TN 2206, November 1950. TN 2334, April 1951.







AERODYNAMICS
10 FUNDAMENTAL (1.1)

Supersonic Flow Compressible (Cont.) Liepmann, H. W.; Roshko, A.; and
Dhawan, S.: On Reflection of Shock
Harmon, Sidney M.: Method for Cal- Waves from Boundary Layers. TN
culating Downwash Field Due to 2334, April 1951.
Lifting Surfaces at Subsonic and
Supersonic Speeds. TN 2344, Sinnette, John T., Jr. and Costello,
April 1951. George R.: Possible Application of
Blade Boundary-Layer Control to
Karpovich, E. A. and Frankl, F. I.: Improvement of Design and Off-
Resistance of a Delta Wing in a Design Performance of Axial-Flow
Supersonic Flow. TM 1283, Turbomachines. TN 2371, May
April 1951. 1951.

Chang, Chieh-Chien: Transient Aerody- LAMINAR FLOW
namic Behavior of an Airfoil Due to (1.1.3.1)
Different Arbitrary Modes of Non-
stationary Motions in a Supersonic Lees, Lester: The Stability of the
Flow. TN 2333, April 1951. Laminar Boundary Layer in a
Compressible Fluid. Rept. 876,
1947.
VISCOUS FLOW
Liepmann, Hans W. and Fila,
( .1 Gertrude H. : Investigations of Ef-
fects of Surface Temperature and
Schubauer, G. B. and Skramstad, H. K.: Single Roughness Elements on
Laminar-Boundary-Layer Oscilla- Boundary-Layer Transition.
tions and Transition on a Flat Plate. Rept. 890, 1947.
Rept. 909, 1948.
Chapman, Dean R. and Perkins,
Kuethe, A. M.; McKee, P. B.; and Edward W.: Experimental Investiga-
Curry, W. H.: Measurements in tion of the Effects of Viscosity on the
the Boundary Layer of a Yawed Drag of Bodies of Revolution at a
Wing. TN 1946, September 1949. Mach Number of 1. 5. RM A7A31a,
April 1947.
Allen, H. Julian: Pressure Distribution
and Some Effects of Viscosity on Scherrer, Richard; Wimbrow, William R.;
Slender Inclined Bodies of Revolu- and Gowen, Forrest E.: Heat-
tion. TN 2044, March 1950. Transfer and Boundary-Layer
Transition on a Heated 200 Cone
Sanger, Eugen: The Gas Kinetics of at a Mach Number of 1. 53. RM
Very High Flight Speeds. TM 1270, A8L28, February 1949.
May 1950.
Donaldson, Coleman duP. and Sullivan,
Szablewski, W.: The Diffusion of a Hot Roger D.: The Effect of Wall Fric-
Air Jet in Air in Motion. TM 1288, tion on the Strength of Shock Waves
December 1950. in Tubes and Hydraulic Jumps in
Channels. TN 1942, September
Furlong, G. Chester and Fitzpatrick, 1949.
James E.: Effects of Mach Number
up to 0. 34 and Reynolds Number up Quick, August Wilhelm and Schrbder,
to 8 x 106 on the Maximum Lift Co- K.: Behavior of the Laminar
efficient of a Wing of NACA 66- Boundary Layer for Periodically
Series Airfoil Sections. TN 2251, Oscillating Pressure Variation.
December 1950. TM 1228, September 1949.

Mager, Artur: Generalization of Loftin, Laurence K., Jr. and Burrows,
Boundary-Layer Momentum- Dale L.: Investigations Relating to
Integral Equations to Three- the Extension of Laminar Flow by
Dimensional Flows Including Those Means of Boundary-Layer Suction
of Rotating System. TN 2310, through Slots. TN 1961, October
March 1951. 1949.








AERODYNAMICS
FUNDAMENTAL (1. 1) 11

Laminar Flow Viscous (Cont.) Roy, Maurice: Theoretical Investigations
on the Efficiency and the Conditions
Wimbrow, William R.: Experimental for the Realization of Jet Engines.
Investigation of Temperature Re- TM 1259, June 1950.
covery Factors on Bodies of Revo-
lution at Supersonic Speeds. TN Mangler, W.: General Solution of
1975, October 1949. Prandtl's Boundary-Layer Equation.
TM 1278, June 1950.
Chapman, Dean R.: Laminar Mixing
of a Compressible Fluid. Rept. Stalder, Jackson R.; Rubesin, Morris W.;
958, 1950. and Tendeland, Thorval: A Deter-
mination of the Laminar-, Transi-
Lessen, Martin: On the Stability of the tional-, and Turbulent-Boundary-
Free Laminar Boundary Layer Layer Temperature-Recovery Fac-
between Parallel Streams. Rept. tors on a Flat Plate in Supersonic
979, 1950. Flow. TN 2077, June 1950.

Klunker, E. B. and Ivey, H. Reese: Blue, Robert E.: Interferometer Cor-
An Analysis of Supersonic Aero- rections and Measurements of
dynamic Heating with Continuous Laminar Boundary Layer in Super-
Fluid Injection. Rept. 990, 1950. sonic Stream. TN 2110, June 1950.

Stiiper: Flight Experiences and Tests Scherrer, Richard: Boundary-Layer
on Two Airplanes with Suction Transition on a Cooled 200 Cone at
Slots. TM 1232, January 1950. Mach Numbers of 1. 5 and 2.0.
TN 2131, July 1950.
Blasius, H.: The Boundary Layers in
Fluids with Little Friction. TM Schlichting, H.: Turbulence and Heat
1256, February 1950. Stratification. TM 1262, October
1950.
Schlichting, H.: Amplitude Distribution
and Energy Balance of Small Dis- Peterson, Robert F.: The Boundary-
turbances in Plate Flow. TM Layer and Stalling Characteristics
1265, April 1950. of the NACA 64A010 Airfoil Section.
TN 2235, November 1950.
Scherrer, Richard and Gowen, Forrest E.:
Comparison of Theoretical and Ex- Stalder, Jackson R. and Slack, Ellis G.:
perimental Heat Transfer on a The Use of a Luminescent Lacquer
Cooled 200 Cone with a Laminar for the Visual Indication of Boundary-
Boundary Layer at a Mach Number Layer Transition. TN 2263, Janu-
of 2.02. TN 2087, May 1950. ary 1951.

Braslow, Albert L. and Visconti, Moore, Franklin K.: Three-Dimensional
Fioravante: Further Experimental Compressible Laminar Boundary-
Studies of Area Suction for the Layer Flow. TN 2279, March 1951.
Control of the Laminar Boundary
Layer on a Porous Bronze NACA Liepmann, H. W.; Roshko, A.; and
64A010 Airfoil. TN 2112, May Dhawan, S.: On Reflection of Shock
1950. Waves from Boundary Layers.
TN 2334, April 1951.
Schuh, H.: The Solution of the Laminar-
Boundary-Layer Equation for the Bursnall, William J. and Loftin,
Flat Plate for Velocity and Tempera- Laurence K., Jr.: Experimental
ture Fields for Variable Physical Investigation of Localized Regions
Properties and for the Diffusion of Laminar-Boundary-Layer Sepa-
Field at High Concentration. TM ration. TN 2338, April 1951.
1275, May 1950.







AERODYNAMICS
12 FUNDAMENTAL (1.1)

Laminar Flow Viscous (Cont.) Gooderum, Paul B.; Wood, George P.;
and Brevoort, Maurice J.: Investi-
Higgins, Robert W. and Pappas, gation with an Interferometer of the
Constantine C.: An Experimental Turbulent Mixing of a Free Super-
Investigation of the Effect of Sur- sonic Jet. Rept. 963, 1950.
face Heating on Boundary-Layer
Transition on a Flat Plate in Su- Schubauer, G. B.; Spangenberg, W. G.;
personic Flow. TN 2351, April and Klebanoff, P. S.: Aerodynamic
1951. Characteristics of Damping Screens.
TN 2001, January 1950.
Struminsky, V. V.: Sideslip in a
Viscous Compressible Gas. TM Tucker, Maurice: Approximate Turbu-
1276, April 1951. lent Boundary-Layer Development
in Plane Compressible Flow along
Borodin, V. A. and Digyakin, Y. F.: Thermally Insulated Surfaces with
Unstable Capillary Waves on Sur- Application to Supersonic-Tunnel
face of Separation of Two Viscous Contour Correction. TN 2045,
Fluids. TM 1281, April 1951. March 1950.

Shvets, M. E.: Method of Successive Schlichting, H.: Amplitude Distribution
Approximations for the Solution and Energy Balance of Small Dis-
of Certain Problems in Aerody- turbances in Plate Flow. TM 1265,
namics. TM 1286, April 1951. April 1950.

TURBULENT FLOW Ludwieg, H.: Instrument for Measuring
(1.1.3.2) the Wall Shearing Stress of Turbu-
lent Boundary Layer. TM 1284,
Chapman, Dean R. and Perkins, May 1950.
Edward W.: Experimental Investi-
gation of the Effects of Viscosity Ludwieg, H. and Tillmann, W.: Investi-
on the Drag of Bodies of Revolution gations of the Wall-Shearing Stress
at a Mach Number of 1. 5. RM in Turbulent Boundary Layers. TM
A7A31a, April 1947. 1285, May 1950.

Zalovcik, John A. and Luke, Ernest P.: Stalder, Jackson R.; Rubesin, Morris W.;
Some Flight Measurements of and Tendeland, Thorval: A Deter-
Pressure-Distribution and Boundary- mination of the Laminar-, Transi-
Layer Characteristics in the Pres- tional-, and Turbulent-Boundary-
ence of Shock. RM L8C22, July Layer Temperature-Recovery Fac-
1948. tors on a Flat Plate in Supersonic
Flow. TN 2077, June 1950.
Scherrer, Richard; Wimbrow,
William R.; and Gowen, Forrest E.: Laufer, John: Investigation of Turbulent
Heat-Transfer and Boundary-Layer Flow in a Two-Dimensional Channel.
Transition on a Heated 200 Cone at TN 2123, July 1950.
a Mach Number of 1. 53. RM
A8L28, February 1949. Deissler, Robert G.: Analytical and
Experimental Investigation of Adia-
Prandtl, L.: Report on Investigation of batic Turbulent Flow in Smooth Tubes.
Developed Turbulence. TM 1231, TN 2138, July 1950.
September 1949.
Schubauer, G. B. and Klebanoff, P. S.:
Wimbrow, William R.: Experimental Investigation of Separation of the
Investigation of Temperature Re- Turbulent Boundary Layer. TN
covery Factors on Bodies of Revo- 2133, August 1950.
lution at Supersonic Speeds. TN
1975, October 1949.








AERODYNAMICS
FUNDAMENTAL (1.1) 13

Turbulent Flow Viscous (Cont.) Shvets, M. E.: Method of Successive
Approximations for the Solution of
Tetervin, Neal and Lin, Chia Chiao: Certain Problems in Aerodynamics.
A General Integral Form of the TM 1286, April 1951.
Boundary-Layer Equation for
Incompressible Flow with an Ap- Liepmann, H. W.; Roshko, A.; and
plication to the Calculation of the Dhawan, S.: On Reflection of Shock
Separation Point of Turbulent Waves from Boundary Layers. TN
Boundary Layers. TN 2158, 2334, April 1951.
August 1950.
Tucker, Maurice: Approximate Calcula-
Brinich, Paul F.: Boundary-Layer tion of Turbulent Boundary-Layer
Measurements in 3. 84- by 10- Development in Compressible Flow.
Inch Supersonic Channel. TN TN 2337, April 1951.
2203, October 1950.
Bursnall, William J. and Loftin,
Schlichting, H.: Turbulence and Heat Laurence K., Jr.: Experimental
Stratification. TM 1262, October Investigation of Localized Regions
1950. of Laminar-Boundary-Layer Sepa-
ration. TN 2338, April 1951.
Nikuradse, J.: Laws of Flow in Rough
-Pipes. TM 1292, November 1950. Rubesin, Morris W.: The Effect of an
Arbitrary Surface-Temperature
Peterson, Robert F.: The Boundary- Variation along a Flat Plate on the
Layer and Stalling Characteristics Convective Heat Transfer in an In-
of the NACA 64A010 Airfoil Section. compressible Turbulent Boundary
TN 2235, November 1950. Layer. TN 2345, April 1951.

Deissler, Robert G.: Analytical Investi- Higgins, Robert W. and Pappas,
gation of Turbulent Flow in Smooth Constantine C.: An Experimental
Tubes with Heat Transfer with Investigation of the Effect of Sur-
Variable Fluid Properties for face Heating on Boundary-Layer
Prandtl Number of 1. TN 2242, Transition on a Flat Plate in Su-
December 1950. personic Flow. TN 2351, April
1951.
Tillmann, W.: Additional Measurements
of the Drag of Surface Irregularities Little, Barney H., Jr. and Wilbur,
in Turbulent Boundary Layers. TM Stafford W.: Turbulence-Intensity
1299, January 1951. Measurements in a Jet of Air Issu-
ing from a Long Tube. TN 2361,
Stalder, Jackson R. and Slack, Ellis G.: May 1951.
The Use of a Luminescent Lacquer
for the Visual Indication of Boundary- JET MIXING
Layer Transition. TN 2263, Janu- (1.1.3.3)
ary 1951.
Callaghan, Edmund E. and Bowden,
Tucker, Maurice and Maslen, Stephen H.: Dean T.: Investigation of Flow Co-
Turbulent Boundary-Layer Tempera- efficient of Circular, Square, and
ture Recovery Factors in Two- Elliptical Orifices at High Pressure
Dimensional Supersonic Flow. TN Ratios. TN 1947, September 1949.
2296, February 1951.
Prandtl, L.: Report on Investigation of
Rubesin, Morris W.; Maydew, Randall C.; Developed Turbulence. TM 1231,
and Varga, Steven A.: An Analyti- September 1949.
cal and Experimental Investigation
of the Skin Friction of the Turbulent Gooderum, Paul B.; Wood, George P.;
Boundary Layer on a Flat Plate at and Brevoort, Maurice J.: Investi-
Supersonic Speeds. TN 2305, gation with an Interferometer of the
February 1951. Turbulent Mixing of a Free Super-
sonic Jet. Rept. 963, 1950.







AERODYNAMICS
14 FUNDAMENTAL (1.1)

Jet Mixing Viscous (cont.) AERODYNAMICS WITH HEAT
Lessen, Martin: On the Stability of the
Free Laminar Boundary Layer be- 1.1.4)
tween Parallel Streams. Rept. 979,
1950. Wimbrow, William R.: Experimental In-
vestigation of Temperature Recovery
Corrsin, Stanley and Uberoi, Mahinder S.: Factors on Bodies of Revolution at
Further Experiments on the Flow and Supersonic Speeds. TN 1975,
Heat Transfer in a Heated Turbulent October 1949.
Air Jet. Rept. 998, 1950.
Scherrer, Richard and Gowen, Forrest E.:
Ruggeri, Robert S.; Callaghan, Comparison of Theoretical and Ex-
Edmund E.; and Bowden, Dean T.: perimental Heat Transfer on a
Penetration of Air Jets Issuing from Cooled 200 Cone with a Laminar
Circular, Square, and Elliptical Boundary Layer at a Mach Number
Orifices Directed Perpendicularly of 2.02. TN 2087, May 1950.
to an Air Stream. TN 2019,
February 1950. Stalder, Jackson R.; Rubesin, Morris W.;
and Tendeland, Thorval: A Deter-
Corrsin, Stanley and Uberoi, Mahinder S.: mination of the Laminar-, Transi-
Spectrums and Diffusion in a Round tional-, and Turbulent-Boundary-
Turbulent Jet. TN 2124, July 1950. Layer Temperature-Recovery Fac-
tors on a Flat Plate in Supersonic
Chelko, Louis J.: Penetration of Liquid Flow. TN 2077, June 1950.
Jets into a High-Velocity Air Stream.
RM E50F21, August 1950. Scherrer, Richard: Boundary-Layer
Transition on a Cooled 200 Cone at
Szablewski, W.: The Diffusion of a Hot Mach Numbers of 1. 5 and 2. 0. TN
Air Jet in Air in Motion. TM 1288, 2131, July 1950.
December 1950.
Wimbrow, William R. and Scherrer,
Liepmann, H. W.; Roshko, A.; and Richard: Laminar-Boundary-Layer
Dhawan, S.: On Reflection of Shock Heat-Transfer Characteristics of a
Waves from Boundary Layers. TN Body of Revolution with a Pressure
2334, April 1951. Gradient at Supersonic Speeds. TN
2148, August 1950.
Bursnall, William J. and Loftin,
Laurence K., Jr.: Experimental Ivey, H. Reese and Cline, Charles W.:
Investigation of Localized Regions Effect of Heat-Capacity Lag on the
of Laminar-Boundary-Layer Sepa- Flow through Oblique Shock Waves.
ration. TN 2338, April 1951. TN 2196, October 1950.

Borodin, V. A. and Digyakin, Y. F.: Stalder, Jackson R.; Goodwin, Glen; and
Unstable Capillary Waves on Sur- Creager, Marcus O.: A Comparison
face of Separation of Two Viscous of Theory and Experiment for High-
Fluids. TM 1281, April 1951. Speed Free-Molecule Flow. TN
2244, December 1950.
Little, Barney H., Jr. and Wilbur,
Stafford W.: Turbulence-Intensity Rubesin, Morris W.: The Effect of an
Measurements in a Jet of Air Issu- Arbitrary Surface-Temperature
ing from a Long Tube. TN 2361, Variation along a Flat Plate on the
May 1951. Convective Heat Transfer in an In-
compressible Turbulent Boundary
Layer. TN 2345, April 1951.








AERODYNAMICS
FUNDAMENTAL (1.1) 15

Aerodynamics with Heat (Cont.) Blue, Robert E.: Interferometer Correc-
tions and Measurements of Laminar
Higgins, Robert W. and Pappas, Boundary Layer in Supersonic Stream.
Constantine C.: An Experimental TN 2110, June 1950.
Investigation of the Effect of Sur-
face Heating on Boundary-Layer Neel, Carr B., Jr. and Bright, Loren G.:
Transition on a Flat Plate in The Effect of Ice Formations on Pro-
Supersonic Flow. TN 2351, peller Performance. TN 2212,
April 1951. October 1950.

HEATING Tucker, Maurice and Maslen, Stephen H.:
(1.1.4.1) Turbulent Boundary-Layer Tempera-
ture Recovery Factors in Two-
Scherrer, Richard: The Effects of Aero- Dimensional Supersonic Flow. TN
dynamic Heating and Heat Transfer 2296, February 1951.
on the Surface Temperature of a
Body of Revolution in Steady Super- HEAT TRANSFER
sonic Flight. Rept. 917, 1948. (1.1.4.2)

Scherrer, Richard; Wimbrow, Scherrer, Richard: The Effects of Aero-
William R.; and Gowen, Forrest E.: dynamic Heating and Heat Transfer
Heat-Transfer and Boundary-Layer on the Surface Temperature of a
Transition on a Heated 200 Cone at Body of Revolution in Steady Super-
a Mach Number of 1. 53. RM sonic Flight. Rept. 917, 1948.
A8L28, February 1949.
Stalder, Jackson R. and Jukoff, David:
Wimbrow, William R.: Experimental Heat Transfer to Bodies Traveling
Investigation of Temperature Re- at High Speed in the Upper Atmos-
covery Factors on Bodies of Revo- phere. Rept. 944, 1949.
lution at Supersonic Speeds. TN
1975, October 1949. Scherrer, Richard; Wimbrow, William R.;
and Gowen, Forrest E.: Heat-
Klunker, E. B. and Ivey, H. Reese: Transfer and Boundary-Layer
An Analysis of Supersonic Aero- Transition on a Heated 200 Cone at
dynamic Heating with Continuous a Mach Number of 1. 53. RM
Fluid Injection. Rept. 990, 1950. A8L28, February 1949.

Scherrer, Richard and Gowen, Wimbrow, William R.: Experimental
Forrest E.: Comparison of Theo- Investigation of Temperature Re-
retical and Experimental Heat covery Factors on Bodies of Revolu-
Transfer on a Cooled 200 Cone tion at Supersonic Speeds. TN 1975,
with a Laminar Boundary Layer October 1949.
at a Mach Number of 2.02. TN
2087, May 1950. Klunker, E. B. and Ivey, H. Reese: An
Analysis of Supersonic Aerodynamic
Schuh, H.: The Solution of the Laminar- Heating with Continuous Fluid Injec-
Boundary-Layer Equation for the tion. Rept. 990, 1950.
Flat Plate for Velocity and Tempera-
ture Fields for Variable Physical Scherrer, Richard and Gowen, Forrest E.:
Properties and for the Diffusion Comparison of Theoretical and Ex-
Field at High Concentration. TM perimental Heat Transfer on a
1275, May 1950. Cooled 200 Cone with a Laminar
Boundary Layer at a Mach Number
Stalder, Jackson R.; Rubesin, of 2.02. TN 2087, May 1950.
Morris W.; and Tendeland, Thorval:
A Determination of the Laminar-,
Transitional-, and Turbulent-
Boundary-Layer Temperature-
Recovery Factors on a Flat Plate
in Supersonic Flow. TN 2077,
June 1950.







AERODYNAMICS
16 FUNDAMENTAL (1.1)

Heat Transfer Aerodynamic (Cont.) Desmon, Leland G. and Sams, Eldon W.:
Correlation of Forced-Convection
Stalder, Jackson R.; Rubesin, Morris W.; Heat-Transfer Data for Air Flowing
and Tendeland, Thorval: A Deter- in Smooth Platinum Tube with Long-
mination of the Laminar-, Transi- Approach Entrance at High Surface
tional-, and Turbulent-Boundary- and Inlet-Air Temperatures. RM
Layer Temperature-Recovery Fac- E50H23, November 1950.
tors on a Flat Plate in Supersonic
Flow. TN 2077, June 1950. Livingood, John N. B. and Brown,
W. Byron: Analysis of Temperature
Corrsin, Stanley and Uberoi, Mahinder S.: Distribution in Liquid-Cooled Tur-
Spectrums and Diffusion in a Round bine Blades. TN 2321, April 1951.
Turbulent Jet. TN 2124, July 1950.
Rubesin, Morris W.: The Effect of an
Gray, Vernon H.: Improvements in Heat Arbitrary Surface-Temperature
Transfer for Anti-Icing of Gas- Variation along a Flat Plate on the
Heated Airfoils with Internal Fins Convective Heat Transfer in an In-
and Partitions. TN 2126, July 1950. compressible Turbulent Boundary
Layer. TN 2345, April 1951.
Schuh, H.: The Solution of the Laminar-
Boundary-Layer Equation for the Shvets, M. E.: Method of Successive
Flat Plate for Velocity and Tempera- Approximations for the Solution of
ture Fields for Variable Physical Certain Problems in Aerodynamics.
Properties and for the Diffusion TM 1286, April 1951.
Field at High Concentration. TM
1275, May 1950. ADDITIONS OF HEAT
(1.1.4.3)
Ludwieg, H.: Instrument for Measuring
the Wall Shearing Stress of Turbu- Liepmann, Hans W. and Fila, Gertrude H.:
lent Boundary Layers. TM 1284, Investigations of Effects of Surface
May 1950. Temperature and Single Roughness
Elements on Boundary-Layer
Wimbrow, William R. and Scherrer, Transition. Rept. 890, 1947.
Richard: Laminar-Boundary-Layer
Heat-Transfer Characteristics of a Scherrer, Richard; Wimbrow, William R.;
Body of Revolution with a Pressure and Gowen, Forrest E.: Heat-
Gradient at Supersonic Speeds. TN Transfer and Boundary-Layer
2148, August 1950. Transition on a Heated 200 Cone at
a Mach Number of 1.53. RM
Manson, S. V.: Correlations of Heat- A8L28, February 1949.
Transfer Data and of Friction Data
for Interrupted Plane Fins Staggered Callaghan, Edmund E. and Bowden,
in Successive Rows. TN 2237, Dean T.: Investigation of Flow Co-
December 1950. efficient of Circular, Square, and
Elliptical Orifices at High Pressure
Deissler, Robert G.: Analytical Investi- Ratios. TN 1947, September 1949.
gation of Turbulent Flow in Smooth
Tubes with Heat Transfer with Vari- Ruggeri, Robert S.; Callaghan, Edmund E.;
able Fluid Properties for Prandtl and Bowden, Dean T.: Penetration of
Number of 1. TN 2242, December Air Jets Issuing from Circular,
1950. Square, and Elliptical Orifices Di-
rected Perpendicularly to an Air
Szablewski, W.: The Diffusion of a Hot Stream. TN 2019, February 1950.
Air Jet in Air in Motion. TM 1288,
December 1950. Scherrer, Richard and Gowen, Forrest E.:
Comparison of Theoretical and Ex-
perimental Heat Transfer on a
Cooled 200 Cone with a Laminar
Boundary Layer at a Mach Number
of 2.02. TN 2087, May 1950.








AERODYNAMICS
FUNDAMENTAL (1.1) 17

Additions of Heat Aerodynamic (Cont.) OW OF RAREFIED GASES

Schuh, H.: The Solution of the Laminar-
Boundary-Layer Equation for the (1..5
Flat Plate for Velocity and Tempera-
ture Fields for Variable Physical Sanger, Eugen: The Gas Kinetics of Very
Properties and for the Diffusion High Flight Speeds. TM 1270, May
Field at High Concentration. TM 1950.
1275, May 1950.
Kane, E. D. and Maslach, G. J.: Impact-
Lowdermilk, Warren H. and Grele, Pressure Interpretation in a Rarefied
Milton D.: Influence of Tube- Gas at Supersonic Speeds. TN 2210,
Entrance Configuration on Average October 1950.
Heat-Transfer Coefficients and
Friction Factors for Air Flowing Stalder, Jackson R.; Goodwin, Glen; and
in an Inconel Tube. RM E50E23, Creager, Marcus O.: A Comparison
August 1950. of Theory and Experiment for High-
Speed Free-Molecule Flow. TN
Pinkel, Benjamin; Noyes, Robert N.; and 2244, December 1950.
Valerino, Michael F.: Method for
Determining Pressure Drop of Air Benson, James M.: The Physical Proper-
Flowing through Constant-Area ties of Active Nitrogen in Low-
Passages for Arbitrary Heat-Input Density Flow. TN 2293, February
Distributions. TN 2186, September 1951.
1950.
FREE MOLECULE FLOW
Kaufman, Samuel J. and Isely, Francis D.: (1.1.5.2)
Preliminary Investigation of Heat
Transfer to Water Flowing in an Stalder, Jackson R. and Jukoff, David:
Electrically Heated Inconel Tube. Heat Transfer to Bodies Traveling
RM E50G31, September 1950. at High Speed in the Upper Atmos-
phere. Rept. 944, 1949.
Pinkel, I. Irving and Serafini, John S.:
Graphical Method for Obtaining Sanger, Eugen: The Gas Kinetics of
Flow Field in a Two-Dimensional Very High Flight Speeds. TM 1270,
Supersonic Stream to which Heat May 1950.
is Added. TN 2206, November 1950.
Stalder, Jackson R.; Goodwin, Glen; and
Desmon, Leland G. and Sams, Eldon W.: Creager, Marcus O.: A Comparison
Correlation of Forced-Convection of Theory and Experiment for High-
Heat-Transfer Data for Air Flowing Speed Free-Molecule Flow. TN 2244,
in Smooth Platinum Tube with Long- December 1950.
Approach Entrance at High Surface
and Inlet-Air Temperatures. RM
E50H23, November 1950.

Valerino, M. F. and Doyle, R. B.:
Method for Determining Pressure
Drop of Monatomic Gases Flowing
in Turbulent Motion through Constant-
Area Passages with Simultaneous
Friction and Heat Addition. TN
2328, April 1951.

Henry, John R. and Bennett, J. Buel:
Method for Calculation of Ram-Jet
Performance. TN 2357, June 1951.







18 AERODYNAMICS






Wings

(1.2)


Gurevich, M. I.: Lift Force of an Arrow- Heaslet, Max. A. and Lomax, Harvard:
Shaped Wing. TM 1245, October Two-Dimensional Unsteady Lift
1949. Problems in Supersonic Flight.
Rept. 945, 1949.

WING SECTIONS Graham, Donald J.: The Development of
Cambered Airfoil Sections Having
(.2.1) Favorable Lift Characteristics at
Supercritical Mach Numbers. Rept.
Rose, Leonard M. and Altman, John M.: 947, 1949.
Low-Speed Investigation of a Thin,
Faired, Double-Wedge Airfoil Sec- Costello, George R.: Method of Designing
tion with Nose Flaps of Various Blades with Prescribed Velocity Dis-
Chords. TN 2018, February 1950. tributions in Compressible Potential
Flows. Rept. 978, 1950.
Vincenti, Walter G.: Comparison be-
tween Theory and Experiment for Bers, Lipman: Velocity Distribution on
Wings at Supersonic Speeds. TN Wing Sections of Arbitrary Shape in
2100, June 1950. Compressible Potential Flow. III -
Circulatory Flows Obeying the Simpli-
Perl, William: Calculation of Transonic fied Density-Speed Relation. TN
Flows past Thin Airfoils by an Inte- 2056, March 1950.
gral Method. TN 2130, July 1950.
Gelbart, Abe and Resch, Daniel: A
Rose, Leonard M. and Altman, John M.: Method of Computing Subsonic Flows
Low-Speed Investigation of the Stall- around Given Airfoils. TN 2057,
ing of a Thin, Faired, Double-Wedge March 1950.
Airfoil with Nose Flap. TN 2172,
August 1950. Bers, Lipman: On the Continuation of a
Potential Gas Flow across the Sonic
SECTION THEORY Line. TN 2058, April 1950.
(1.2.1.1)
Barmby, J. G.; Cunningham, H. J.; and
Eggers, A. J., Jr.: Aerodynamic Char- Garrick, I. E.: Study of Effects of
acteristics at Subcritical and Super- Sweep on the Flutter of Cantilever
critical Mach Numbers of Two Air- Wings. TN 2121, June 1950.
foil Sections having Sharp Leading
Edges and Eatreme Rearward Posi- Perl, William: Calculation of Transonic
tions of Maximum Thickness. RM Flows past Thin Airfoils by an Inte-
A7C10, November 1947. gral Method. TN 2130, July 1950.

Loftin, Laurence K., Jr.: Theoretical Amick, James L.: Comparison of the
and Experimental Data for a Number Experimental Pressure Distribution
of NACA 6A-Series Airfoil Sections. on an NACA 0012 Profile at High
Rept. 903, 1948. Speeds with that Calculated by the
Relaxation Method. TN 2174,
Czarnecki, K. R. and Schueller, C. F.: August 1950.
Investigation of Interaction Effects
Arising from Sids-Wall Boundary Ivey, H. Reese aid Cline, Charles W.:
ILayers in Supersonic Wind-Tunnel Effect of Heat-Capacity Lag on the
Tests of Airfoils. RM L8G27, Flow through Oblique Shock Waves.
November 1948. TN 2196, October 1950.







AERODYNAMICS
WINGS (1.2) 19

Section Theory Wing (Cont.) Camber
(1. 2.1. 2.1)
Czarnecki, K. R. and Mueller, James N.:
An Approximate Method of Calculat- Loftin, Laurence K., Jr.: Theoretical
ing Pressures in the Tip Region of a and Experimental Data for a Number
Rectangular Wing of Circular-Arc of NACA 6A-Series Airfoil Sections.
Section at Supersonic Speeds. TN Rept. 903, 1948.
2211, October 1950.
Graham, Donald J.: The Development of
Goin, Kennith L.: Equations and Charts Cambered Airfoil Sections Having
for the Rapid Estimation of Hinge- Favorable Lift Characteristics at
Moment and Effectiveness Param- Supercritical Mach Numbers. Rept.
eters for Trailing-Edge Controls 947, 1949.
Having Leading and Trailing Edges
Swept ahead of the Mach Lines. TN Loftin, Laurence K., Jr. and Smith,
2221, November 1950. Hamilton A.: Aerodynamic Charac-
teristics of 15 NACA Airfoil Sections
Harder, Keith C. and Klunker, E. B.: at Seven Reynolds Numbers from
On a Source-Sink Method for the 0. 7 x 106 to 9.0 x 106. TN 1945,
Solution of the Prandtl-Busemann October 1949.
Iteration Equations in Two-
Dimensional Compressible Flow. Loftin, Laurence K., Jr. and Bursnall,
TN 2253, December 1950. William J.: The Effects of Variations
in Reynolds Number between 3. 0 x
Spreiter, John R.: Similarity Laws for 106 and 25. 0 x 106 upon the Aerody-
Transonic Flow about Wings of namic Characteristics of a Number
Finite Span. TN 2273, January 1951. of NACA 6-Series Airfoil Sections.
Rept. 964, 1950.
Graham, David: A Modification to Thin-
Airfoil-Section Theory, Applicable Summers, James L. and Treon, Stuart L.:
to Arbitrary Airfoil Sections, to Ac- The Effects of Amount and Type of
count for the Effects of Thickness on Camber on the Variation with Mach
the Lift Distribution. TN 2298, Number of the Aerodynamic Char-
February 1951. acteristics of a 10-Percent-Thick
NACA 64A-Series Airfoil Section.
Vincenti, Walter G. and Wagoner, Cleo B.: TN 2096, May 1950.
Transonic Flow past a Wedge Profile
with Detached Bow Wave General McCullough, George B. and Haire,
Analytical Method and Final Calcu- William M.: Low-Speed Character-
lated Results. TN 2339, April 1951. istics of Four Cambered, 10-Percent-
Thick NACA Airfoil Sections. TN
Klunker, E. B. and Harder, Keith C.: 2177, August 1950.
On the Second-Order Tunnel-Wall-
Constriction Corrections in Two- Graham, David: A Modification to Thin-
Dimensional Compressible Flow. Airfoil-Section Theory, Applicable
TN 2350, April 1951. to Arbitrary Airfoil Sections, to Ac-
count for the Effects of Thickness on
SECTION VARIABLES the Lift Distribution. TN 2298,
(1.2.1.2) February 1951.

Gendler, Sel and Johnson, Donald F.: Thickness
Determination of Minimum Moments (1.2.1. 2. 2)
of Inertia of Arbitrarily Shaped Areas,
such as Hollow Turbine Blades. RM Hamilton, William T. and Nelson,
E9H10, February 1950. Warren H.: Summary Report on the
High-Speed Characteristics of Six
Kelly, John A.: Effects of Modifications Model Wings having NACA 651-
to the Leading-Edge Region on the Series Sections. Rept. 877, 1947.
Stalling Characteristics of the NACA
631-012 Airfoil Section. TN 2228,
November 1950.







AERODYNAMICS
20 WINGS (1.2)

Thickness Wing Sections (Cont.) Vincenti, Walter G. and Wagoner, Cleo B.:
Transonic Flow past a Wedge Profile
Graham, Donald J.: The Development with Detached Bow Wave General
of Cambered Airfoil Sections having Analytical Method and Final Calculated
Favorable Lift Characteristics at Results. TN 2339, April 1951.
Supercritical Mach Numbers. Rept.
947, 1949. Thickness Distribution
(1.2.1. 2. 3)
Loftin, Laurence K., Jr. and Smith,
Hamilton A.: Aerodynamic Charac- Eggers, A. J., Jr.: Aerodynamic Char-
teristics of 15 NACA Airfoil Sections acteristics at Subcritical and Super-
at Seven Reynolds Numbers from critical Mach Numbers of Two Air-
0.7 x 106 to 9.0 x 106. TN 1945, foil Sections having Sharp Leading
October 1949. Edges and Extreme Rearward Posi-
tions of Maximum Thickness. RM
Loftin, Laurence K., Jr. and Bursnall, A7C10, November 1947.
William J. : The Effects of Varia-
tions in Reynolds Number between Loftin, Laurence K., Jr.: Theoretical
3.0 x 106 and 25.0 x 106 upon the and Experimental Data for a Number
Aerodynamic Characteristics of a of NACA 6A-Series Airfoil Sections.
Number of NACA 6-Series Airfoil Rept. 903, 1948.
Sections. Rept. 964, 1950.
Zalovcik, John A. and Luke, Ernest P.:
Kainer, Julian H.: Theoretical Calcula- Some Flight Measurements of
tions of the Supersonic Pressure Pressure-Distribution and Boundary-
Distribution and Wave Drag for a Layer Characteristics in the Pres-
Limited Family of Tapered Swept- ence of Shock. RM L8C22, July
back Wings with Symmetrical Para- 1948.
bolic-Arc Sections at Zero Lift.
TN 2009, January 1950. Graham, Donald J.: The Development of
Cambered Airfoil Sections Having
Smith, Hamilton A. and Schaefer, Favorable Lift Characteristics at
Raymond F.: Aerodynamic Charac- Supercritical Mach Numbers. Rept.
teristics at Reynolds Numbers of 947, 1949.
3.0 x 106 and 6.0 x 106 of Three
Airfoil Sections Formed by Cutting Loftin, Laurence K., Jr. and Smith,
off Various Amounts from the Rear Hamilton A.: Aerodynamic Charac-
Portion of the NACA 0012 Airfoil teristics of 15 NACA Airfoil Sec-
Section. TN 2074, April 1950. tions at Seven Reynolds Numbers
from 0. 7 x 106 to 9.0x 106. TN
Czarnecki, K. R. and Mueller, James N.: 1945, October 1949.
An Approximate Method of Calculat-
ing Pressures in the Tip Region of Loftin, Laurence K., Jr. and Bursnall,
a Rectangular Wing of Circular-Arc William J.: The Effects of Variations
Section at Supersonic Speeds. TN in Reynolds Number between 3. 0 x
2211, October 1950. 106 and 25.0 x 106 upon the Aerody-
namic Characteristics of a Number
Goin, Kennith L.: Equations and Charts of NACA 6-Series Airfoil Sections.
for the Rapid Estimation of Hinge- Rept. 964, 1950.
Moment and Effectiveness Param-
eters for Trailing-Edge Controls Smith, Hamilton A. and Schaefer,
Having Leading and Trailing Edges Raymond F.: Aerodynamic Charac-
Swept ahead of the Mach Lines. teristics at Reynolds Numbers of
TN 2221, November 1950. 3.0 x 106 and 6.0 x 106 of Three
Airfoil Sections Formed by Cutting
Graham, David: A Modification to Thin- off Various Amounts from the Rear
Airfoil-Section Theory, Applicable Portion of the NACA 0012 Airfoil
to Arbitrary Airfoil Sections, to Ac- Section. TN 2074, April 1950.
count for the Effects of Thickness on
the Lift Distribution. TN 2298,
February 1951.







AERODYNAMICS
WINGS (1.2) 21

Thickness Distribution Wing Sections Horton, Elmer A.; Racisz, Stanley F.;
(Cont.) and Paradiso, Nicholas J.: Investi-
McCullough, George B. and Haire, gation of Boundary-Layer Control to
William M.: Low-Speed Character- Improve the Lift and Drag Character-
istics of Four Cambered, 10- istics of the NACA 652-415 Airfoil
Percent-Thick NACA Airfoil Sec- Section with Double Slotted and Plain
tions. TN 2177, August 1950. Flaps. TN 2149, August 1950.

Inlets and Exits McCullough, George B. and Haire,
(1.2.1.2.4) William M.: Low-Speed Characteris-
tics of Four Cambered, 10-Percent-
Perl, William and Moses, H. E.: Thick NACA Airfoil Sections. TN
Velocity Distributions on Two- 2177, August 1950.
Dimensional Wing-Duct Inlets
by Conformal Mapping. Rept. Tillmann, W.: Additional Measurements
893, 1948. of the Drag of Surface Irregularities
in Turbulent Boundary Layers. TM
Ruden, P.: Two-Dimensional Symmetri- 1299, January 1951.
cal Inlets with External Compression.
TM 1279, March 1950. Gowan, William H., Jr. and Mulholland,
Donald R.: Effectiveness of Thermal-
Brdel, Walter: Theory of Plane, Sym- Pneumatic Airfoil-Ice-Protection
metrical Inlet Diffusers. TM 1267, System. RM E50K10a, April 1951.
April 1950.
DESIGNATED PROFILES
Surface Conditions (1.2.1.3)
(1. 2. 1. 2. 5)
Racisz, Stanley F.: Experimental Investi-
Quinn, John H., Jr.: Summary of Drag gation of the Effectiveness of Various
Characteristics of Practical- Suction-Slot Arrangements as a
Construction Wing Sections. Rept. Means for Increasing the Maximum
910, 1948. Lift of the NACA 653-018 Airfoil
Section. RM L50A10, March 1950.
Loftin, Laurence K., Jr. and Smith,
Hamilton A.: Aerodynamic Charac- Horton, Elmer A.; Racisz, Stanley F.;
teristics of 15 NACA Airfoil Sec- and Paradiso, Nicholas J.: Investi-
tions at Seven Reynolds Numbers gation of Boundary-Layer Control
from 0. 7 x 106 to 9.0 x 106. TN to Improve the Lift and Drag Char-
1945, October 1949. acteristics of the NACA 652-415
Airfoil Section with Double Slotted
Schaefer, Raymond F. and Smith, and Plain Flaps. TN 2149, August
Hamilton A.: Aerodynamic Charac- 1950.
teristics of the NACA 8-H-12 Air-
foil Section at Six Reynolds Num- HIGH LIFT DEVICES
bers from 1.8 x 106 to 11.0 x 106. (1.2.1.4)
TN 1998, December 1949.
McCullough, George B. and Gault,
Loftin, Laurence K., Jr. and Bursnall, Donald E.: An Experimental Investi-
William J.: The Effects of Varia- gation of the NACA 631-012 Airfoil
tions in Reynolds Number between Section with Leading-Edge and Mid-
3.0 x 106 and 25.0 x 106 upon the chord Suction Slots. TN 2041,
Aerodynamic Characteristics of a February 1950.
Number of NACA 6-Series Airfoil
Sections. Rept. 964, 1950. Plain Flaps
(1. 2. 1. 4. 1)
Smith, Hamilton A. and Schaefer,
Raymond F.: Aerodynamic Charac- Cahill, Jones F.: Summary of Section
teristics at Reynolds Numbers of Data on Trailing-Edge High-Lift
3.0 x 106 and 6.0 x 106 of Three Air- Devices. Rept. 938, 1949.
foil Sections formed by Cutting Off
Various Amounts from the Rear
Portion of the NACA 0012 Airfoil
Section. TN 2074, April 1950.






AERODYNAMICS
22 WINGS (1.2)

Plain Flaps Ring Sections (Cont.) McCullough, George B. and Haire,
William M.: Low-Speed Character-
Graham, Donald J.: The Development istics of Four Cambered, 10-Percent-
of Cambered Airfoil Sections Having Thick NACA Airfoil Sections. TN
Favorable Lift Characteristics at 2177, August 1950.
Supercritical Mach Numbers. Rept.
947, 1949. Slotted Flaps
(1.2.1.4.3)
Rose, Leonard M. and Altman, John M.:
Low-Speed Investigation of a Thin, Cahill, Jones F.: Summary of Section
Faired, Double-Wedge Airfoil Sec- Data on Trailing-Edge High-Lift
tion with Nose Flaps of Various Devices. Rept. 938, 1949.
Chords. TN 2018, February 1950.
Horton, Elmer A.; Racisz, Stanley F.;
Rose, Leonard M. and Altman, John M.: and Paradiso, Nicholas J.: Investiga-
Low-Speed Investigation of the Stall- tion of Boundary-Layer Control to
ing of a Thin, Faired, Double-Wedge Improve the Lift and Drag Character-
Airfoil with Nose Flap. TN 2172, istics of the NACA 652-415 Airfoil
August 1950. Section with Double Slotted and Plain
Flaps. TN 2149, August 1950.
Goin, Kennith L.: Equations and Charts
for the Rapid Estimation of Hinge- Leading Edge Flaps
Moment and Effectiveness Param- (1. 2. 1.4.4)
eters for Trailing-Edge Controls
Having Leading and Trailing Edges Rose, Leonard M. and Altman, John M.:
Swept ahead of the Mach Lines. Low-Speed Investigation of a Thin,
TN 2221, November 1950. Faired, Double-Wedge Airfoil Sec-
tion with Nose Flaps of Various
DeYoung, John: Theoretical Symmetric Chords. TN 2018, February 1950.
Span Loading Due to Flap Deflection
for Wings of Arbitrary Plan Form at Rose, Leonard M. and Altman, John M.:
Subsonic Speeds. TN 2278, January Low-Speed Investigation of the Stall-
1951. ing of a Thin, Faired, Double-
Wedge Airfoil with Nose Flap. TN
Split Flaps 2172, August 1950.
(1. 2. 1.4. 2)
Kelly, John A. : Effects of Modifications
Cahill, Jones F.: Summary of Section to the Leading-Edge Region on the
Data on Trailing-Edge High-Lift Stalling Characteristics of the NACA
Devices. Rept. 938, 1949. 631-012 Airfoil Section. TN 2228,
November 1950.
Stephenson, Jack D.: The Effects of
Aerodynamic Brakes upon the Speed CONTROLS
Characteristics of Airplanes. TN (1.2.1.5)
1939, September 1949.
Phillips, William H.: Appreciation and
Loftin, Laurence K., Jr. and Smith, Prediction of Flying Qualities. Rept.
Hamilton A.: Aerodynamic Charac- 927, 1949.
teristics of 15 NACA Airfoil Sec-
tions at Seven Reynolds Numbers Flap Type
from 0. 7 x 106 to 9. x 106. TN (1.2.1.5.1)
1945, October 1949.
Goin, Kennith L.: Equations and Charts
Loftin, Laurence K., Jr. and Bursnall, for the Rapid Estimation of Hinge-
William J.: The Effects of Varia- Moment and Effectiveness Param-
tions in Reynolds Number between eters for Trailing-Edge Controls
3. 0 x 106 and 25. 0 x 106 upon the Having Leading and Trailing Edges
Aerodynamic Characteristics of a Swept ahead of the Mach Line. TN
Number of NACA 6-Series Airfoil 2221, November 1950.
Sections. Rept. 964, 1950.








AERODYNAMICS
WINGS (1.2) 23

BOUNDARY LAYER Braslow, Albert L. and Visconti,
(1. 2. 1.6) Fioravante: Further Experimental
Studies of Area Suction for the Con-
Lees, Lester: The Stability of the trol of the Laminar Boundary Layer
Laminar Boundary Layer in a on a Porous Bronze NACA 64A010
Compressible Fluid. Rept. 876, Airfoil. TN 2112, May 1950.
1947.
Horton, Elmer A.; Racisz, Stanley F.;
Eggers, A. J., Jr.: Aerodynamic Char- and Paradiso, Nicholas J.: Investi-
acteristics at Subcritical and Super- gation of Boundary-Layer Control to
critical Mach Numbers of Two Air- Improve the Lift and Drag Character-
foil Sections having Sharp Leading istics of the NACA 652-415 Airfoil
Edges and Extreme Rearward Posi- Section with Double Slotted and Plain
tions of Maximum Thickness. RM Flaps. TN 2149, August 1950.
A7C10, November 1947.
Peterson, Robert F.: The Boundary-
Schubauer, G. B. and Skramstad, H. K.: Layer and Stalling Characteristics
Laminar-Boundary-Layer Oscilla- of the NACA 64A010 Airfoil Section.
tions and Transition pn a Flat Plate. TN 2235, November 1950.
Rept. 909, 1948.
Liepmann, H. W.; Roshko, A.; and
Zalovcik, John A. and Luke, Ernest P.: Dhawan, S.: On Reflection of Shock
Some Flight Measurements of Waves from Boundary Layers. TN
Pressure-Distribution and Boundary- 2334, April 1951.
Layer Characteristics in the Pres-
ence of Shock. RM L8C22, July Tucker, Maurice: Approximate Calcula-
1948. tion of Turbulent Boundary-Layer
Development in Compressible Flow.
Kuethe, A. M.; McKee, P. B.; and TN 2337, April 1951.
Curry, W. H.: Measurements in
the Boundary Layer of a Yawed Characteristics
Wing. TN 1946, September 1949. (1. 2.1.6.1)

Loftin, Laurence K., Jr. and Burrows, Blue, Robert E.: Interferometer Correc-
Dale L.: Investigations Relating tions and Measurements of Laminar
to the Extension of Laminar Flow Boundary Layer in Supersonic
by Means of Boundary-Layer Suc- Stream. TN 2110, June 1950.
tion through Slots. TN 1961,
October 1949. Mangler, W.: General Solution of
Prandtl's Boundary-Layer Equa-
Loftin, Laurence K., Jr. and Bursnall, tion. TM 1278, June 1950.
William J.: The Effects of Varia-
tions in Reynolds Number between Tetervin, Neal and Lin, Chia Chiao:
3. 0 x 106 and 25. 0 x 106 upon the A General Integral Form of the
Aerodynamic Characteristics of a Boundary-Layer Equation for In-
Number of NACA 6-Series Airfoil compressible Flow with an Appli-
Sections. Rept. 964, 1950. cation to the Calculation of the
Separation Point of Turbulent
McCullough, George B. and Gault, Boundary Layers. TN 2158,
Donald E.: An Experimental Inves- August 1950.
tigation of the NACA 631-012 Air-
foil Section with Lefling-Edge and Rose, Leonard M. and Altman, John M.:
Midchord Suction Slots. TN 2041, Low-Speed Investigation of the Stall-
February 1950. ing of a Thin, Faired, Double-
Wedge Airfoil with Nose Flap.
Tucker, Maurice: Approximate Turbu- TN 2172, August 1950.
lent Boundary-Layer Development
in Plane Compressiblle Flow along Bursnall, William J. and Loftin,
Thermally Insulated Surfaces with Laurence K., Jr. : Experimental
Application to Supersonic-Tunnel Investigation of Localized Regions
Coritour Correction. TN 2045, of Laminar-Boundary-Layer Sepa-
March 1950. ration. TN 2338, April 1951.







AERODYNAMICS
24 WINGS (1.2)

Control Horton, Elmer A.; Racisz, Stanley F.;
(1.2. 1. 6. 2) and Paradiso, Nicholas J.: Investi-
gation of Boundary-Layer Control to
Racisz, Stanley F.: Experimental Inves- Improve the Lift and Drag Character-
tigation of the Effectiveness of istics of the NACA 652-415 Airfoil
Various Suction-Slot Arrangements Section with Double Slotted and Plain
as a Means for Increasing the Maxi- Flaps. TN 2149, August 1950.
mum Lift of the NACA 653-018
Airfoil Section. RM L50A10, March Bursnall, William J. and Loftin,
1950. Laurence K., Jr.: Experimental
Investigation of Localized Regions
REYNOLDS NUMBER EFFECTS of Laminar-Boundary-Layer Separa-
(1.2.1.7) tion. TN 2338, April 1951.

Lees, Lester: The Stability of the MACH NUMBER EFFECTS
Laminar Boundary Layer in a (1.2.1.8)
Compressible Fluid. Rept. 876,
1947. Lees, Lester: The Stability of the
Laminar Boundary Layer in a
Loftin, Laurence K., Jr. and Smith, Compressible Fluid. Rept. 876,
Hamilton A.: Aerodynamic Charac- 1947.
teristics of 15 NACA Airfoil Sec-
tions at Seven Reynolds Numbers Eggers, A. J., Jr.: Aerodynamic Char-
from 0.7 x 106 to 9.0 x 106. TN acteristics at Subcritical and Super-
1945, October 1949. critical Mach Numbers of Two Air-
foil Sections having Sharp Leading
Schaefer, Raymond F. and Smith, Edges and Extreme Rearward Posi-
Hamilton A.: Aerodynamic Char- tions of Maximum Thickness. RM
acteristics of the NACA 8-H-12 A7C10, November 1947.
Airfoil Section at Six Reynolds
Numbers from 1.8 x 100 to 11.0 x Zalovcik, John A. and Luke, Ernest P.:
106. TN 1998, December 1949. Some Flight Measurements of
Pressure-Distribution and Boundary-
Loftin, Laurence K., Jr. and Bursnall, Layer Characteristics in the Pres-
William J.: The Effects of Varia- ence of Shock. RM L8C22, July
tions in Reynolds Number between 1948.
3. 0 x 106 and 25. 0 x 106 upon the
Aerodynamic Characteristics of a Graham, Donald J.: The Development of
Number of NACA 6-Series Airfoil Cambered Airfoil Sections Having
Sections. Rept. 964, 1950. Favorable Lift Characteristics at
Supercritical Mach Numbers. Rept.
Klunker, E. B. and Ivey, H. Reese: An 947, 1949.
Analysis of Supersonic Aerodynamic
Heating with Continuous Fluid Injec- Costello, George R.: Method of Design-
tion. Rept. 990, 1950. ing Blades with Prescribed Velocity
Distributions in Compressible Poten-
Racisz, Stanley F.: Experimental Inves- tial Flows. Rept. 978, 1950.
tigation of the Effectiveness of
Various Suction-Slot Arrangements Klunker, E. B. and Ivey, H. Reese: An
as a Means for Increasing the Maxi- Analysis of Supersonic Aerodynamic
mum Lift of the NACA 653-018 Air- Heating with Continuous Fluid Injec-
foil Section. RM L50A10, March tion. Rept. 990, 1950.
1950.
Kainer, Julian H.: Theoretical Calcula-
Smith, Hamilton A. and Schaefer, tions of the Supersonic Pressure Dis-
Raymond F.: Aerodynamic Charac- tribution and Wave Drag for a Lim-
teristics at Reynolds Numbers of ited Family of Tapered Sweptback
3. 0 x 106 and 6. 0 x 106 of Three Air- Wings with Symmetrical Parabolic-
foil Sections Formed by Cutting off Arc Sections at Zero Lift. TN
Various Amounts from the Rear 2009, January 1950.
Portion of the NACA 0012 Airfoil
Section. TN 2074, April 1950.







AERODYNAMICS
WINGS (1.2) 25
Mach No. Effeots Wing Sections (Cont.)

WING THEORY
Summers, James L. and Treon, (1.2.2.1)
Stuart L.: The Effects of Amount
and Type of Camber on the Varia- Heaslet, Max. A.; Lomax, Harvard; and
tion with Mach Number of the Aero- Jones, Arthur L.: Volterra's Solu-
dynamic Characteristics of a 10- tion of the Wave Equation as Applied
Percent-Thick NACA 64A-Series to Three-Dimensional Supersonic Air-
Airfoil Section. TN 2096, May foil Problems. Rept. 889, 1947.
1950.
Brown, Clinton E. and Adams, Mac C.:
Perl, William: Calculation of Transonic Damping in Pitch and Roll of Tri-
Flows past Thin Airfoils by an Inte- angular Wings at Supersonic Speeds.
gral Method. TN 2130, July 1950. Rept. 892, 1948.

Amick, James L.: Comparison of the Heaslet, Max. A. and Lomax, Harvard:
Experimental Pressure Distribu- The Use of Source-Sink and Doublet
tion on an NACA 0012 Profile at Distributions Extended to the Solu-
High Speeds with that Calculated tion of Arbitrary Boundary Value
by the Relaxation Method. TN 2174, Problems in Supersonic Flow. Rept.
August 1950. 900, 1948.

Ivey, H. Reese and Cline, Charles W.: Jones, Robert T.: Subsonic Flow over
Effect of Heat-Capacity Lag on the Thin Oblique Airfoils at Zero Lift.
Flow through Oblique Shock Waves. Rept. 902, 1948.
TN 2196, October 1950.
Swanson, Robert S. and Crandall,
Vincenti, Walter G. and Wagoner, Stewart M.: Lifting-Surface-Theory
Cleo B.: Transonic Flow past a Aspect-Ratio Corrections to the Lift
Wedge Profile with Detached Bow and Hinge-Moment Parameters for
Wave General Analytical Method Full-Span Elevators on Horizontal
and Final Calculated Results. TN Tail Surfaces. Rept. 911, 1948.
2339, April 1951.
DeYoung, John and Harper, Charles W.:
Klunker, E. B. and Harder, Keith C.: Theoretical Symmetric Span Loading
On the Second-Order Tunnel-Wall- at Subsonic Speeds for Wings Having
Constriction Corrections in Two- Arbitrary Plan Form. Rept. 921,
Dimensional Compressible Flow. 1948.
TN 2350, April 1951.
Harmon, Sidney M. : Stability Derivatives
COMPLETE WINGS of Thin Rectangular Wings at Super-
sonic Speeds. Wing Diagonals ahead
(1.2.2) of Tip Mach Lines. Rept. 925, 1949.

Lomax, Harvard and Heaslet, Max. A.:
Ellis, Macon C., Jr. and Hasel, Damping-in-Roll Calculations for
Lowell E.: Preliminary Investi- Slender Swept-Back Wings and
gation at Supersonic Speeds of Tri- Slender Wing-Body Combinations.
angular and Sweptback Wings. TN TN 1950, September 1949.
1955, October 1949.
Diederich, Franklin W. and Zlotnick,
Cohen, Doris: Formulas and Charts Martin: Theoretical Spanwise Lift
for the Supersonic Lift and Drag Distributions of Low-Aspect-Ratio
of Flat Swept-Back Wings with Wings at Speeds below and above
Interacting Leading and Trailing the Speed of Sound. TN 1973,
Edges. TN 2093, May 1950. October 1949.

Jones, Robert T.: The Spanwise Distri- Piland, Robert 0.: Summary of the
bution of Lift for Minimum Induced Theoretical Lift, Damping-in-Roll,
Drag of Wings having a Given Lift and Center-of-Pressure Character-
and a Given Bending Moment. TN istics of Various Wing Plan Forms
2249, December 1950. at Supersonic Speeds. TN 1977,
October 1949.







AERODYNAMICS
26 WINGS (1. 2)

Theory Complete Wings (Cont.) Malvestuto, Frank S., Jr. and Margolis,
Kenneth: Theoretical Stability
Gurevich, M. I.: Lift Force of an Derivatives of Thin Sweptback Wings
Arrow-Shaped Wing. TM 1245, Tapered to a Point with Sweptback or
October 1949. Swetforward Trailing Edges for a
Limited Range of Supersonic Speeds.
Lomax, Harvard and Heaslet, Max. A.: Rept. 971, 1950.
Linearized Lifting-Surface Theory
for Swept-Back Wings with Slender Mirels, Harold and Haefeli, Rudolph C.:
Plan Forms. TN 1992, December Line-Vortex Theory for Calculation
1949. of Supersonic Downwash. Rept. 983,
1950.
Evvard, John C.: Use of Source Dis-
tributions for Evaluating Theo- Brown, Clinton E.: The Reversibility
retical Aerodynamics of Thin Theorem for Thin Airfoils in Sub-
Finite Wings at Supersonic sonic and Supersonic Flow. Rept.
Speeds. Rept. 951, 1950. 986, 1950.

Heaslet, Max. A.; Lomax, Harvard; Lagerstrom, P.A.: Linearized Super-
and Spreiter, John R.: Linearized sonic Theory of Conical Wings.
Compressible-Flow Theory for TN 1685, January 1950.
Sonic Flight Speeds. Rept. 956,
1950. Jones, Arthur L. and Alksne, Alberta:
The Load Distribution Due to Side-
Heaslet, Max. A. and Lomax, Harvard: slip on Triangular, Trapezoidal,
The Calculation of Downwash behind and Related Plan Forms in Super-
Supersonic Wings with v.n Applica- sonic Flow. TN 2007, January
tion to Triangular Plan Forms. 1950.
Rept. 957, 1950.
Kainer, Julian H.: Theoretical Calcu-
Heaslet, Max. A. and Lomax, Harvard: lations of the Supersonic Pressure
The Application of Green's Theorem Distribution and Wave Drag for a
to the Solution of Boundary-Value Limited Family of Tapered Swept-
Problems in Linearized Supersonic back Wings with Symmetrical
Wing Theory. Rept. 961, 1950. Parabolic-Arc Sections at Zero
Lift. TN 2009, January 1950.
Spreiter, John R.: The Aerodynamic
Forces on Slender Plane- and DeYoung, John: Spanwise Loading for
Cruciform-Wing and Body Combi- Wings and Control Surfaces of Low
nations. Rept. 962, 1950. Aspect Ratio. TN 2011, January
1950.
Bird, John D.: Some Theoretical Low-
Speed Span Loading Characteristics Moskowitz, Barry and Moeckel, W. E.:
of Swept Wings in Roll and Sideslip. First-Order Theory for Unsteady
Rept. 969, 1950. Motion of Thin Wings at Supersonic
Speeds. TN 2034, February 1950.
Malvestuto, Frank S., Jr.; Margolis,
Kenneth; and Ribner, Herbert S.: Walker, Harold J. and Ballantyne,
Theoretical Lift and Damping in Mary B.: Pressure Distribution
Roll at Supersonic Speeds of Thin and Damping in Steady Roll at
Sweptback Tapered Wings with Supersonic Mach Numbers of
Streamwise Tips, Subsonic Lead- Flat Swept-Back Wings with Sub-
ing Edges and Supersonic Trailing sonic Edges. TN 2047, March
Edges. Rept. 970, 1950. 1950.







AERODYNAMICS
WINGS (1.2) 27

Theory Complete ,ings (Cont.) Harmon, Sidney M. and Martin, John C.:
Theoretical Calculations of the
Margolis, Kenneth: Theoretical Lift and Lateral Force and Yawing Moment
Damping in Roll of Thin Sweptback Due to Rolling at Supersonic Speeds
Tapered Wings with Raked-In and for Sweptback Tapered Wings with
Cross-Stream Wing Tips at Super- Streamwise Tips. Supersonic
sonic Speeds. Subsonic Leading Leading Edges. TN 2156, July 1950.
Edges. TN 2048, March 1950.
Haefeli, Rudolph C.; Mirels, Harold; and
Harmon, Sidney M. and Jeffreys, Cummings, John L.: Charts for
Isabella: Theoretical Lift and Estimating Downwash behind Rectangu-
Damping in Roll of Thin Wings lar, Trapezoidal, and Triangular
with Arbitrary Sweep and Taper Wings at Supersonic Speeds. TN
at Supersonic Speeds. Supersonic 2141, August 1950.
Leading and Trailing Edges. TN
2114, May 1950. Mirels, Harold: Lift-Cancellation Tech-
nique in Linearized Supersonic Wing
Vincenti, Walter G.: Comparison be- Theory. TN 2145, August 1950.
tween Theory and Experiment for
Wings at Supersonic Speeds. TN Ribner, Herbert S.: On the Effect of
2100, June 1950. Subsonic Trailing Edges on Damping
in Roll and Pitch of Thin Sweptback
Barmby, J. G.; Cunningham, H. J.; and Wings in a Supersonic Stream. TN
Garrick, I. E.: Study of Effects 2146, August 1950.
of Sweep on the Flutter of Cantilever
Wings. TN 2121, June 1950. Ribner, Herbert S.: Some Conical and
Quasi-Conical Flows in Linearized
Margolis, Kenneth: Theoretical Calcu- Supersonic-Wing Theory. TN 2147,
lations of the Lateral Force and August 1950.
Yawing Moment Due to Rolling at
Supersonic Speeds for Sweptback Walker, Harold J. and Ballantyne,
Tapered Wings with Streamwise Mary B.: Pressure Distribution and
Tips. Subsonic Leading Edges. Damping in Steady Pitch at Super-
TN 2122, June 1950. sonic Mach Numbers of Flat Swept-
Back Wings having all Edges Sub-
Diederich, Franklin W.: Approximate sonic. TN 2197, October 1950.
Aerodynamic Influence Coefficients
for Wings of Arbitrary Plan Form Czarnecki, K. R. and Mueller, James N.:
in Subsonic Flow. TN 2092, July An Approximate Method of Calculat-
1950. ing Pressures in the Tip Region of a
Rectangular Wing of Circular-Arc
Martin, John C.: The Calculation of Section at Supersonic Speeds. TN
Downwash behind Wings of Arbitrary 2211, October 1950.
Plan Form at Supersonic Speeds.
TN 2135, July 1950. Goin, Kennith L.: Equations and Charts
for the Rapid Estimation of Hinge-
DeYoung, John: Theoretical Antisym- Moment and Effectiveness Param-
metric Span Loading for Wings of eters for Trailing-Edge Controls
Arbitrary Plan Form at Subsonic having Leading and Trailing Edges
Speeds. TN 2140, July 1950. Swept ahead of the Mach Lines.
TN 2221, November 1950.
Tucker, Warren A. and Piland, Robert 0.:
Estimation of the Damping in Roll Jones, Robert T.: The Spanwise Distri-
of Supersonic-Leading-Edge Wing- bution of Lift for Minimum Induced
Body Combinations. TN 2151, July Drag of Wings having a Given Lift
1950. and a Given Bending Moment. TN
2249, December 1950.







AERODYNAMICS
28 WINGS (1.2)

Theory Complete Wings (Cont.) Malvestuto, Frank S., Jr. and Hoover,
Dorothy M.: Lift and Pitching
Lomax, Harvard; Heaslet, Max. A.; and Derivatives of Thin Sweptback
Fuller, Franklyn B : Formulas for Tapered Wings with Streamwise
Source, Doublet, and Vortex Distri- Tips and Subsonic Leading Edges
butions in Supersonic Wing Theory. at Supersonic Speeds. TN 2294,
TN 2252, December 1950. February 1951.

Lomax, Harvard; Heaslet, Max. A.; and Lomax, Harvard and Sluder, Loma:
Fuller, Franklyn B.: Three- Chordwise and Compressibility Cor-
Dimensional, Unsteady-Lift Prob- rections to Slender-Wing Theory.
lems in High-Speed Flight Basic TN 2295, February 1951.
Concepts. TN 2256, December 1950.
Skoog, Richard B. and Brown, Harvey H.:
Lampert, Seymour: Rolling and Yawing A Method for the Determination of
Moments for Swept-Back Wings in the Spanwise Load Distribution of a
Sideslip at Supersonic Speeds. TN Flexible Swept Wing at Subsonic
2262, January 1951. Speeds. TN 2222, March 1951.

Adams, Gaynor J.: Theoretical Damping Harmon, Sidney M.: Correspondence
in Roll and Rolling Effectiveness of Flows for Wings in Linearized
Slender Cruciform Wings. TN 2270, Potential Fields at Subsonic and
January 1951. Supersonic Speeds. TN 2303,
March 1951.
Spreiter, John R.: Similarity Laws for
Transonic Flow about Wings of Malvestuto, Frank S., Jr. and Hoover,
Finite Span. TN 2273, January 1951. Dorothy M.: Supersonic Lift and
Pitching Moment of Thin Sweptback
DeYoung, John: Theoretical Symmetric Tapered Wings Produced by Constant
Span Loading Due to Flap Deflection Vertical Acceleration. Subsonic
for Wings of Arbitrary Plan Form at Leading Edges and Supersonic Trail-
Subsonic Speeds. TN 2278, January ing Edges. TN 2315, March 1951.
1951.
Chang, Chieh-Chien: Applications of Von
Sivells, James C.: An Improved Ap- Karman's Integral Method in Super-
proximate Method for Calculating sonic Wing Theory. TN 2317,
Lift Distributions Due to Twist. March 1951.
TN 2282, January 1951.
Chang, Chieh-Chien: Transient Aerody-
Sivells, James C. and Westrick, namic Behavior of an Airfoil Due to
Gertrude C.: Method for Calculating Different Arbitrary Modes of Non-
Lift Distributions for Unswept Wings stationary Motions in a Supersonic
with Flaps or Ailerons by Use of Flow. TN 2333, April 1951.
Nonlinear Section Lift Data. TN
2283, January 1951. Diederich, Franklin W.: A Plan-Form
Parameter for Correlating Certain
Hopkins, Edward J.: Lift, Pitching Aerodynamic Characteristics of
Moment, and Span Load Character- Swept Wings. TN 2335, April 1951.
istics of Wings at Low Speed as Af-
fected by Variations of Sweep and Piland, Robert 0.: Some Theoretical
Aspect Ratio. TN 2284, January Characteristics of Trapezoidal
1951. Wings in Supersonic Flow and a
Comparison of Several Wing-Flap
Ribner, Herbert S.: Damping in Roll of Combinations. TN 2336, April
Cruciform and Some Related Delta 1951.
Wings at Supersonic Speeds. TN
2285, February 1951. Harmon, Sidney M.: Method for Calcu-
lating Downwash Field Due to Lifting
Surfaces at Subsonic and Supersonic
Speeds. TN 2344, April 1951.








AERODYNAMICS
WINGS (1.2) 29

Theory Complete Wings (Cont.) Hassell, James L. and Bennett,
Charles V.: The Dynamic Lateral
Diederich, Franklin W.: Charts and Control Characteristics of Airplane
Tables for Use in Calculations of Models Having Unswept Wings with
Downwash of Wings of Arbitrary Round- and Sharp-Leading-Edge
Plan Form. TN 2353, May 1951. Sections. TN 2219, November 1950.

WING VARIABLES Aspect Ratio
(1.2.2.2) (1.2. 2.2.2)

Lovell, J. Calvin and Lipson, Stanley: Hamilton, William T. and Nelson,
An Analysis of the Effect of Lift- Warren H.: Summary Report on the
Drag Ratio and Stalling Speed on High-Speed Characteristics of Six
Landing-Flare Characteristics. Model Wings having NACA 651-
TN 1930, September 1949. Series Sections. Rept. 877, 1947.

Cohen, Doris: Theoretical Loading at Heaslet, Max. A.; Lomax, Harvard; and
Supersonic Speeds of Flat Swept- Jones, Arthur L.: Volterra's Solu-
Back Wings with Interacting Trail- tion of the Wave Equation as Applied
ing and Leading Edges. TN 1991, to Three-Dimensional Supersonic
December 1949. Airfoil Problems. Rept. 889, 1947.

Lagerstrom, P. A.: Linearized Super- Purser, Paul E. and Spearman, M. Leroy:
sonic Theory of Conical Wings. Wind-Tunnel Tests at Low Speed of
TN 1685, January 1950. Swept and Yawed Wings having Vari-
ous Plan Forms. RM L7D23, May
Gendler, Sel and Johnson, Donald F.: 1947.
Determination of Minimum Moments
of Inertia of Arbitrarily Shaped Areas Adler, Alfred A.: Effects of Combina-
Such as Hollow Turbine Blades. tions of Aspect Ratio and Sweepback
RM E9H10, February 1950. at High Subsonic Mach Numbers.
RM L7C24, June 1947.
Vincenti, Walter G.: Comparison be-
tween Theory and Experiment for Brown, Clinton E. and Adams, Mac C.:
Wings at Supersonic Speeds. TN Damping in Pitch and Roll of Tri-
2100, June 1950. angular Wings at Supersonic Speeds.
Rept. 892, 1948.
Michael, William H., Jr.: Analysis of
the Effects of Wing Interference on Swanson, Robert S. and Crandall,
the Tail Contributions to the Rolling Stewart M.: Lifting-Surface-Theory
Derivatives. TN 2332, April 1951. Aspect-Ratio Corrections to the Lift
and Hinge-Moment Parameters for
Klinar, Walter J. and Wilson, Jack H.: Full-Span Elevators on Horizontal
Spin-Tunnel Investigation of the Ef- Tail Surfaces. Rept. 911, 1948.
fects of Mass and Dimensional
Variations on the Spinning Charac- DeYoung, John and Harper, Charles W.:
teristics of a Low-Wing Single- Theoretical Symmetric Span Loading
Vertical-Tail Model Typical of at Subsonic Speeds for Wings having
Personal-Owner Airplanes. TN Arbitrary Plan Forms. Rept. 921,
2352, May 1951. 1948.

Profiles Stack, John and Lindsey, W. F.: Char-
(1. 2. 2. 2.1) acteristics of Low-Aspect-Ratio
Wings at Supercritical Mach Num-
Sivells, James C. and Spooner, Stanley H.: bers. Rept. 922, 1949.
Investigation in the Langley 19-Foot
Pressure Tunnel of Two Wings of
NACA 65-210 and 64-210 Airfoil
Sections with Various Type Flaps.
Rept. 942, 1949.







AERODYNAMICS
30 WINGS (1.2)

Aspect Ratio Complete Wings (Cont.) Tucker, Warren A. and Nelson,
Robert L.: The Effect of Torsional
Harmon, Sidney M.: Stability Deriva- Flexibility on the Rolling Character-
tives of Thin Rectangular Wings at istics at Supersonic Speeds of
Supersonic Speeds. Wing Diagonals Tapered Unswept Wings. Rept.
ahead of Tip Mach Lines. Rept. 972, 1950.
925, 1949.
Jones, Arthur L. and Alksne, Alberta:
Harmon, Sidney M.: Theoretical Rela- The Load Distribution Due to Sideslip
tions between the Stability Deriva- on Triangular, Trapezoidal, and Re-
tives of a Wing in Direct and in Re- lated Plan Forms in Supersonic
verse Supersonic Flow. TN 1943, Flow. TN 2007, January 1950.
September 1949.
Kainer, Julian H.: Theoretical Calcula-
Diederich, Franklin W. and Zlotnick, tions of the Supersonic Pressure
Martin: Theoretical Spanwise Lift Distribution and Wave Drag for a
Distributions of Low-Aspect-Ratio Limited Family of Tapered Swept-
Wings at Speeds below and above back Wings with Symmetrical
the Speed of Sound. TN 1973, Parabolic-Arc Sections at Zero Lift.
October 1949. TN 2009, January 1950.

Piland, Robert 0.: Summary of the DeYoung, John: Spanwise Loading for
Theoretical Lift, Damping-in- Wings and Control Surfaces of Low
Roll, and Center-of-Pressure Aspect Ratio. TN 2011, January
Characteristics of Various Wing 1950.
Plan Forms at Supersonic Speeds.
TN 1977, October 1949. Margolis, Kenneth: Theoretical Lift and
Damping in Roll of Thin Sweptback
Cohen, Doris: Theoretical Loading at Tapered Wings with Raked-In and
Supersonic Speeds of Flat Swept- Cross-Stream Wing Tips at Super-
Back Wings with Interacting Trail- sonic Speeds. Subsonic Leading
ing and Leading Edges. TN 1991, Edges. TN 2048, March 1950.
December 1949.
Watkins, Charles E. : Effect of Aspect
Goodman, Alex and Fisher, Lewis R.: Ratio on the Air Forces and Moments
Investigation at Low Speeds of the of Harmonically Oscillating Thin
Effect of Aspect Ratio and Sweep Rectangular Wings in Supersonic
on Rolling Stability Derivatives of Potential Flow. TN 2064, April 1950.
Untapered Wings. Rept. 968, 1950.
Cohen, Doris: Formulas and Charts for
Bird, John D.: Some Theoretical Low- the Supersonic Lift and Drag of Flat
Speed Span Loading Characteristics Swept-Back Wings with Interacting
of Swept Wings in Roll and Sideslip. Leading and Trailing Edges. TN
Rept. 969, 1950. 2093, May 1950.

Malvestuto, FrankS., Jr.; Margolis, Harmon, Sidney M. and Jeffreys,
Kenneth; and Ribner, Herbert S.: Isabella: Theoretical Lift and Damp-
Theoretical Lift and Damping in ing in Roll of Thin Wings with Arbi-
Roll at Supersonic Speeds of Thin trary Sweep and Taper at Supersonic
Sweptback Tapered Wings with Speeds. Supersonic Leading and
Streamwise Tips, Subsonic Lead- Trailing Edges. TN 2114, May 1950.
ing Edges and Supersonic Trailing
Edges. Rept. 970, 1950. Margolis, Kenneth: Theoretical Calcula-
tions of the Lateral Force and Yawing
Malvestuto, Frank S., Jr. and Margolis, Moment Due to Rolling at Supersonic
Kenneth: Theoretical Stability Speeds for Sweptback Tapered Wings
Derivatives of Thin Sweptback Wings with Streamwise Tips. Subsonic
Tapered to a Point with Sweptback Leading Edges. TN 2122, June 1950.
or Sweptforward Trailing Edges for
a Limited Range of Supersonic
Speeds. Rept. 971, 1950.








AERODYNAMICS
WINGS (1.2) 31

Aspect Ratio Complete Wings (Cont.) Diederich, Franklin W.: A Plan-Form
Parameter for Correlating Certain
DeYoung, John: Theoretical Antisym- Aerodynamic Characteristics of
metric Span Loading for Wings of Swept Wings. TN 2335, April 1951.
Arbitrary Plan Form at Subsonic
Speeds. TN 2140, July 1950. Fischel, Jack and Hagerman, John R.:
Effect of Aspect Ratio and Sweepback
Harmon, Sidney M. and Martin, John C.: on the Low-Speed Lateral Control
Theoretical Calculations of the Characteristics of Untapered Low-
Lateral Force and Yawing Moment Aspect-Ratio Wings Equipped with
Due to Rolling at Supersonic Speeds Retractable Ailerons. TN 2347,
for Sweptback Tapered Wings with May 1951.
Streamwise Tips. Supersonic Lead-
ing Edges. TN 2156, July 1950. Naeseth, Rodger L. and O'Hare,
William M.: Effect of Aspect Ratio
Horton, Elmer A.; Loftin, Laurence K., on the Low-Speed Lateral Control
Jr.; and Racisz, Stanley F.: Analy- Characteristics of Unswept Un-
sis of the Effects of Boundary-Layer tapered Low-Aspect-Ratio Wings.
Control on the Power-Off Landing TN 2348, May 1951.
Performance Characteristics of a
Liaison Type of Airplane. TN Sweep
2143, August 1950. (1.2.2.2.3)

Riebe, John M. and Watson, James M.: Van Dyke, Milton D.: Aerodynamic Char-
The Effect of End Plates on Swept acteristics Including Scale Effects of
Wings at Low Speed. TN 2229, Several Wings and Bodies alone and
November 1950. in Combination at a Mach Number of
1.53. RM A6K22, December 1946.
DeYoung, John: Theoretical Symmetric
Span Loading Due to Flap Deflection Garrick, I. E. and Rubinow, S. I.:
for Wings of Arbitrary Plan Form Theoretical Study of Air Forces on
at Subsonic Speeds. TN 2278, an Oscillating or Steady Thin Wing
January 1951. in a Supersonic Main Stream.
Rept. 872, 1947.
Hopkins, Edward J.: Lift, Pitching
Moment, and Span Load Character- Heaslet, Max. A.; Lomax, Harvard; and
istics of Wings at Low Speed as Af- Jones, Arthur L.: Volterra's Solu-
fected by Variations of Sweep and tion of the Wave Equation as Applied
Aspect Ratio. TN 2284, January to Three-Dimensional Supersonic
1951. Airfoil Problems. Rept. 889, 1947.

Lomax, Harvard and Sluder, Loma: Wilson, Herbert A., Jr. and Lovell,
Chordwise and Compressibility J. Calvin: Full-Scale Investigation
Corrections to Slender-Wing of the Maximum Lift and Flow Char-
Theory. TN 2295, February 1951. acteristics of an Airplane having
Approximately Triangular Plan Form.
Malvestuto, Frank S., Jr. and Hoover, RM L6K20, February 1947.
Dorothy M.: Lift and Pitching
Derivatives of Thin Sweptback Purser, Paul E. and Spearman, M. Leroy:
Tapered Wings with Streamwise Wind-Tunnel Tests.at Low Speed of
Tips and Subsonic Leading Edges Swept and Yawed Wings having Vari-
at Supersonic Speeds. TN 2294, ous Plan Forms. RM L7D23, May
February 1951. 1947.

Malvestuto, Frank S., Jr. and Hoover, Adler, Alfred A.: Effects of Combina-
Dorothy M.: Supersonic Lift and tions of Aspect Ratio and Sweepback
Pitching Moment of Thin Sweptback at High Subsonic Mach Numbers. RM
Tapered Wings Produced by Constant L7C24, June 1947.
Vertical Acceleration. Subsonic
Leading Edges and Supersonic Trail-
ing Edges. TN 2315, March 1951.







AERODYNAMICS
32 WINGS (1.2)

Sweep Gomplete flings (Cont.) Piland, Robert 0.: Summary of the
Theoretical Lift, Damping-in-Roll,
Liccini, Luke L.: Effects of 450 Sweep- and Center-of-Pressure Character-
back on the High-Speed Character- istics of Various Wing Plan Forms
istics of a Wing having a Modified at Supersonic Speeds. TN 1977,
NACA 16-012 Airfoil Section. RM October 1949.
L6K18a, July 1947.
Cohen, Doris: Theoretical Loading at
Brown, Clinton E. and Adams, Mac C.: Supersonic Speeds of Flat Swept-
Damping in Pitch and Roll of Tri- Back Wings with Interacting Trail-
angular Wings at Supersonic Speeds. ing and Leading Edges. TN 1991,
Rept. 892, 1948. December 1949.

Jones, Robert T.: Subsonic Flow over Lomax, Harvard and Heaslet, Max. A.:
Thin Oblique Airfoils at Zero Lift. Linearized Lifting-Surface Theory
Rept. 902, 1948. for Swept-Back Wings with Slender
Plan Forms. TN 1992, December
DeYoung, John and Harper, Charles W.: 1949.
Theoretical Symmetric Span Load-
ing at Subsonic Speeds for Wings Goodman, Alex and Fisher, Lewis R.:
Having Arbitrary Plan Forms. Investigation at Low Speeds of the
Rept. 921, 1948. Effect of Aspect Ratio and Sweep
on Rolling Stability Derivatives of
Harmon, Sidney M.: Theoretical Rela- Untapered Wings. Rept. 968, 1950.
tions between the Stability Deriva-
tives of a Wing in Direct and in Re- Bird, John D.: Some Theoretical Low-
verse Supersonic Flow. TN 1943, Speed Span Loading Characteristics
September 1949. of Swept Wings in Roll and Sideslip.
Rept. 969, 1950.
Kuethe, A. M.; McKee, P. B.; and
Curry, W. H.: Measurements in Malvestuto, Frank S., Jr.; Margolis,
the Boundary Layer of a Yawed Kenneth; and Ribner, Herbert S.:
Wing. TN 1946, September 1949. Theoretical Lift and Damping in
Roll at Supersonic Speeds of Thin
Dods, Jules B., Jr.: Wind-Tunnel In- Sweptback Tapered Wings with
vestigation of Horizontal Tails. Streamwise Tips, Subsonic Leading
V 450 Swept-Back Plan Form of Edges and Supersonic Trailing Edges.
Aspect Ratio 2. RM A9D05, Rept. 970, 1950.
September 1949.
Malvestuto, Frank S., Jr. and Margolis,
Ellis, Macon C., Jr. and Hasel, Kenneth: Theoretical Stability
Lowell E.: Preliminary Investiga- Derivatives of Thin Sweptback Wings
tion at Supersonic Speeds of Tri- Tapered to a Point with Sweptback
angular and Sweptback Wings. TN or Sweptforward Trailing Edges for
1955, October 1949. a Limited Range of Supersonic Speeds.
Rept. 971, 1950.
Reise.-t, Thomas D.: Gust-Tunnel In-
vestigation of a Flexible-Wing Mathews, Charles W. and Thompson,
Model with Semichord Line Swept Jim Rogers: Comparative Drag
Back 450. TN 1959, October 1949. Measurements at Transonic Speeds
of Rectangular and Sweptback NACA
Diederich, Franklin W. and Zlotnick, 65-009 Airfoils Mounted on a Freely
Martin: Theoretical Spanwise Lift Falling Body. Rept. 988, 1950.
Distributions of Low-Aspect-Ratio
Wings at Speeds below and above Jones, Arthur L. and Alksne, Alberta:
the Speed of Sound. TN 1973, The Load Distribution Due to Side-
October 1949. slip on Triangular, Trapezoidal,
and Related Plan Forms in Super-
sonic Flow. TN 2007, January 1950.








AERODYNAMICS
WINGS (1.2) 33

Sweep Complete Wings (Cont.) Harmon, Sidney M. and Martin, John C.:
Theoretical Calculations of the
Kainer, Julian H.: Theoretical Calcula- Lateral Force and Yawing Moment
tions of the Supersonic Pressure Due to Rolling at Supersonic Speeds
Distribution and Wave Drag for a for Sweptback Tapered Wings with
Limited Family of Tapered Swept- Streamwise Tips. Supersonic
back Wings with Symmetrical Leading Edges. TN 2156, July 1950.
Parabolic-Arc Sections at Zero
Lift. TN 2009, January 1950. Dannenberg, Robert E.: Measurements
of Section Characteristics of a 450
Brewer, Jack D. and Lichtenstein, Swept Wing Spanning a Rectangular
Jacob H.: Effect of Horizontal Low-Speed Wind Tunnel as Affected
Tail on Low-Speed Static Lateral by the Tunnel Walls. TN 2160,
Stability Characteristics of a August 1950.
Model having 450 Sweptback Wing
and Tail Surfaces. TN 2010, Johnson, Harold S. and Hagerman, John R.:
January 1950. Wind-Tunnel Investigation at Low
Speed of a 450 Sweptback Untapered
Margolis, Kenneth: Theoretical Lift Semispan Wing of Aspect Ratio 1. 59
and Damping in Roll of Thin Swept- Equipped with Various 25-Percent-
back Tapered Wings with Raked-In Chord Plain Flaps. TN 2169,
and Cross-Stream Wing Tips at August 1950.
Supersonic Speeds. Subsonic
Leading Edges. TN 2048, March Pierce, Harold B.: Gust-Tunnel Investi-
1950. gation of a Wing Model with Semi-
chord Line Swept Back 600. TN
Cohen, Doris: Formulas and Charts 2204, October 1950.
for the Supersonic Lift and Drag of
Flat Swept-Back Wings with Inter- Shanks, Robert E.: Model Flight Investi-
acting Leading and Trailing Edges. gation of a Nonlifting Winged Tow
TN 2093, May 1950. Target. RM L50H30, October 1950.

Harmon, Sidney M. and Jeffreys, Riebe, John M. and Watson, James M.:
Isabella: Theoretical Lift and The Effect of End Plates on Swept
Damping in Roll of Thin Wings Wings at Low Speeds. TN 2229,
with Arbitrary Sweep and Taper November 1950.
at Supersonic Speeds. Supersonic
Leading and Trailing Edges. TN Lampert, Seymour: Rolling and Yawing
2114, May 1950. Moments for Swept-Back Wings in
Sideslip at Supersonic Speeds. TN
Barmby, J. G. ; Cunningham, H. J.; 2262, January 1951.
and Garrick, I. E.: Study of Ef-
fects of Sweep on the Flutter of DeYoung, John: Theoretical Symmetric
Cantilever Wings. TN 2121, June Span Loading Due to Flap Deflection
1950. for Wings of Arbitrary Plan Form
at Subsonic Speeds. TN 2278,
Margolis, Kenneth: Theoretical Calcu- January 1951.
lations of the Lateral Force and
Yawing Moment Due to Rolling at Hopkins, Edward J.: Lift, Pitching
Supersonic Speeds for Sweptback Moment, and Span Load Character-
Tapered Wings with Streamwise istics of Wings at Low Speed as Af-
Tips. Subsonic Leading Edges. fected by Variations of Sweep and
TN 2122, June 1950. Aspect Ratio. TN 2284, January
1951.
DeYoung, John: Theoretical Antisym-
metric Span Loading for Wings of Dods, Jules B., Jr.: Estimation of Low-
Arbitrary Plan Form at Subsonic Speed Lift and Hinge-Moment Param-
Speeds. TN 2140, July 1950. eters for Full-Span Trailing-Edge
Flaps on Lifting Surfaces with and
without Sweepback. TN 2288, Febru-
ary 1951.







AERODYNAMICS
34 WINGS (1. 2)

Sweep Complete Wings (Cont.) Brown, Clinton E. and Adams, Mac C.:
Damping in Pitch and Roll of Tri-
Malvestuto, Frank S., Jr. and Hoover, angular Wings at Supersonic Speeds.
Dorothy M.: Lift and Pitching Rept. 892, 1948.
Derivatives of Thin Sweptback
Tapered Wings with Streamwise DeYoung, John and Harper, Charles W.:
Tips and Subsonic Leading Edges Theoretical Symmetric Span Load-
at Supersonic Speeds. TN 2294, ing at Subsonic Speeds for Wings
February 1951. Having Arbitrary Plan Form. Rept.
921, 1948.
Malvestuto, Frank S., Jr. and Hoover,
Dorothy M.: Supersonic Lift and Weil, Joseph and Sleeman, William G., Jr.:
Pitching Moment of Thin Sweptback Prediction of the Effects of Propeller
Tapered Wings Produced by Con- Operation on the Static Longitudinal
stant Vertical Acceleration. Sub- Stability of Single-Engine Tractor
sonic Leading Edges and Super- Monoplanes with Flaps Retracted.
sonic Trailing Edges. TN 2315, Rept. 941, 1949.
March 1951.
Harmon, Sidney M.: Theoretical Rela-
Johnson, Harold S. and Hagerman, tions between the Stability Deriva-
John R.: Wind-Tunnel Investiga- tives of a Wing in Direct and in
tion at Low Speed of Lateral Con- Reverse Supersonic Flow. TN
trol Characteristics of an Un- 1943, September 1949.
tapered 450 Sweptback Semispan
Wing of Aspect Ratio 1. 59 Equipped Diederich, Franklin W. and Zlotnick,
with Various 25-Percent-Chord Martin: Theoretical Spanwise Lift
Plain Ailerons. TN 2316, March Distributions of Low-Aspect-Ratio
1951. Wings at Speeds below and above
the Speed of Sound. TN 1973,
Diederich, Franklin W.: A Plan-Form October 1949.
Parameter for Correlating Certain
Aerodynamic Characteristics of Piland, Robert 0.: Summary of the
Swept Wings. TN 2335, April Theoretical Lift, Damping-in-Roll,
1951. and Center-of-Pressure Character-
istics of Various Wing Plan Forms
Harmon, Sidney M.: Method for Cal- at Supersonic Speeds. TN 1977,
culating Downwash Field Due to October 1949.
Lifting Surfaces at Subsonic and
Supersonic Speeds. TN 2344, Bird, John D.: Some Theoretical Low-
April 1951. Speed Span Loading Characteristics
of Swept Wings in Roll and Sideslip.
Struminsky, V. V.: Sideslip in a Rept. 969, 1950.
Viscous Compressible Gas. TM
1276, April 1951. Malvestuto, Frank S., Jr.; Margolis,
Kenneth; and Ribner, Herbert S.:
Fischel, Jack and Hagerman, John R.: Theoretical Lift and Damping in
Effect of Aspect Ratio and Sweep- Roll at Supersonic Speeds of Thin
back on the Low-Speed Lateral Sweptback Tapered Wings with
Control Characteristics of Un- Streamwise Tips, Subsonic Lead-
tapered Low-Aspect-Ratio Wings ing Edges and Supersonic Trailing
Equipped with Retractable Ailer- Edges. Rept. 970, 1950.
ons. TN 2347, May 1951.
Malvestuto, Frank S., Jr. and Margolis,
Taper and Twist Kenneth: Theoretical Stability
(1. 2.2. 2.4) Derivatives of Thin Sweptback Wings
Tapered to a Point with Sweptback
Purser, Paul E. and Spearman, M. or Sweptforward Trailing Edges for
Leroy: Wind-Tunnel Tests at Low a Limited Range of Supersonic
Speed of Swept and Yawed Wings Speeds. Rept. 971, 1950.
Having Various Plan Forms. RM
L7D23, May 1947.








AERODYNAMICS
WINGS (1. 2) 35

Taper and Twist Complete Wings (Cont.) Riebe, John M. and Watson, James M.:
The Effect of End Plates on Swept
Tucker, Warren A. and Nelson, Wings at Low Speed. TN 2229,
Robert L.: The Effect of Tor- November 1950.
sional Flexibility on the Rolling
Characteristics at Supersonic Lampert, Seymour: Rolling and Yawing
Speeds of Tapered Unswept Wings. Moments for Swept-Back Wings in
Rept. 972, 1950. Sideslip at Supersonic Speeds. TN
2262, January 1951.
Kainer, Julian H. : Theoretical Calcu-
lations of the Supersonic Pressure Sivells, James C.: An Improved Ap-
Distribution and Wave Drag for a proximate Method for Calculating
Limited Family of Tapered Swept- Lift Distributions Due to Twist.
back Wings with Symmetrical TN 2282, January 1951.
Parabolic-Arc Sections at Zero
Lift. TN 2009, January 1950. Malvestuto, Frank S., Jr. and Hoover,
Dorothy M.: Lift and Pitching
Margolis, Kenneth: Theoretical Lift Derivatives of Thin Sweptback
and Damping in Roll of Thin Swept- Tapered Wings with Streamwise
back Tapered Wings and Raked-In Tips and Subsonic Leading Edges
and Cross-Stream Wing Tips at at Supersonic Speeds. TN 2294,
Supersonic Speeds. Subsonic Lead- February 1951.
ing Edges. TN 2048, March 1950.
Malvestuto, Frank S., Jr. and Hoover,
Cohen, Doris: Formulas and Charts Dorothy M.: Supersonic Lift and
for the Supersonic Lift and Drag Pitching Moment of Thin Sweptback
of Flat Swept-Back Wings with Tapered Wings Produced by Con-
Interacting Leading and Trailing stant Vertical Acceleration. Sub-
Edges. TN 2093, May 1950. sonic Leading Edges and Supersonic
Trailing Edges. TN 2315, March
Harmon, Sidney M. and Jeffreys, 1951.
Isabella: Theoretical Lift and
Damping in Roll of Thin Wings Klinar, Walter J. and Wilson, Jack H.:
with Arbitrary Sweep and Taper Spin-Tunnel Investigation of the
at Supersonic Speeds. Supersonic Effects of Mass and Dimensional
Leading and Trailing Edges. TN Variations on the Spinning Charac-
2114, May 1950. teristics of a Low-Wing Single-
Vertical-Tail Model Typical of
Margolis, Kenneth: Theoretical Calcu- Personal-Owner Airplanes. TN
lations of the Lateral Force and 2352, May 1951.
Yawing Moment Due to Rolling at
Supersonic Speeds for Sweptback Surface Conditions
Tapered Wings with Streamwise (1. 2. 2. 2. 6)
Tips. Subsonic Leading Edges.
TN 2122, June 1950. Nissen, James M.; Gadeberg, Burnett L.;
and Hamilton, William T.: Correla-
Martin, John C.: The Calculation of tion of the Drag Characteristics of a
Downwash behind Wings of Arbi- P-51B Airplane Obtained from High-
trary Plan Form at Supersonic Speed Wind Tunnel and Flight Tests.
Speeds. TN 2135, July 1950. Rept. 916, 1948.

Harmon, Sidney M. and Martin, John C.: Sivells, James C. and Spooner, Stanley H.:
Theoretical Calculations of the Investigation in the Langley 19-Foot
Lateral Force and Yawing Moment Pressure Tunnel of Two Wings of
Due to Rolling at Supersonic Speeds NACA 65-210 and 64-210 Airfoil
for Sweptback Tapered Wings with Sections with Various Type Flaps.
Streamwise Tips. Supersonic Rept. 942, 1949.
Leading Edges. TN 2156, July
1950.







AERODYNAMICS
36 WINGS (1.2)

Surface Conditions Complete Sivells, James C. and Spooner, Stanley H..:
N.ings (Cont.) Investigation in the Langley 19-Foot
Dods, Jules B., Jr.: Wind-Tunnel In- Pressure Tunnel of Two Wings of
vestigation of Horizontal Tails. NACA 65-210 and 64-210 Airfoil
V 450 Swept-Back Plan Form Sections with Various Type Flaps.
of Aspect Ratio 2. RM A9D05, Rept. 942, 1949.
September 1949.
Diederich, Franklin W. and Zlotnick,
Furlong, G. Chester and Fitzpatrick, Martin: Theoretical Spanwise Lift
James E.: Effects of Mach Num- Distributions of Low-Aspect-Ratio
ber up to 0. 34 and Reynolds Num- Wings at Speeds below and above
ber up to 8 x 106 on the Maximum the Speed of Sound. TN 1973,
Lift Coefficient of a Wing of NACA October 1949.
66-Series Airfoil Sections. TN
2251, December 1950. Lovell, J. Calvin and Lipson, Stanley:
An Analysis of the Effect of Lift-
Dihedral Drag Ratio and Stalling Speed on
(1. 2. 2. 2. 7) Landing-Flare Characteristics.
TN 1930, September 1949.
Riebe, John M. and Watson, James M.:
The Effect of End Plates on Swept Dods, Jules B., Jr.: Wind-Tunnel
Wings at Low Speed. TN 2229, Investigation of Horizontal Tails.
November 1950. V 450 Swept-Back Plan Form of
Aspect Ratio 2. RM A9D05,
HIGH LIFT DEVICES September 1949.
(1.2.2.3)
Bird, John D. and Jaquet, Byron M.:
Hamilton, William T. and Nelson, A Study of the Use of Experimental
Warren H.: Summary Report on Stability Derivatives in the Calcula-
the High-Speed Characteristics tion of the Lateral Disturbed Mo-
of Six Model Wings having NACA tions of a Swept-Wing Airplane and
651-Series Sections. Rept. 877, Comparison with Flight Results.
1947. TN 2013, January 1950.

Stiiper: Flight Experiences and Tests Johnson, Harold S. and Hagerman, John R.:
on Two Airplanes with Suction Wind-Tunnel Investigation at Low
Slots. TM 1232, January 1950. Speed of an Unswept Untapered
Semispan Wing of Aspect Ratio
Sivells, James and Westrick, Ger- 3.13 Equipped with Various 25-
trude C.: Method for Calculating Percent-Chord Plain Flaps. TN
Lift Distributions for Unswept 2080, April 1950.
Wings with Flaps or Ailerons by
Use of Nonlinear Section Lift Haefeli, Rudolph C.; Mirels, Harold;
Data. TN 2283, January 1951. and Cummings, John L.: Charts
for Estimating Downwash behind
Trailing Edge Flaps Rectangular, Trapezoidal, and
(1. 2. 2. 3.1) Triangular Wings at Supersonic
Speeds. TN 2141, August 1950.
Sawyer, Richard H.: Flight Measure-
ments of the Lateral Control Char- Johnson, Harold S. and Hagerman,
acteristics of Narrow-Chord John R.: Wind-Tunnel Investiga-
Ailerons on the Trailing Edge of tion at Low Speed of a 450 Sweptback
a Full-Span Slotted Flap. Rept. Untapered Semispan Wing of Aspect
883, 1947. Ratio 1. 59 Equipped with Various
25-Percent-Chord Plain Flaps. TN
Purser, Paul E. and Spearman, 2169, August 1950.
M. Leroy: Wind-Tunnel Tests
at Low Speed of Swept and Yawed
Wings having Various Plan Forms.
RM L7D23, May 1947.








AERODYNAMICS
WINGS (1. 2) 37

Trailing Edge Flaps Complete IYings Letko, William: Effect of Vertical-Tail
(Cont.) Area and Length on the Yawing
Kainer, Julian H. and Marte, Jack E.: Stability Characteristics of a Model
Theoretical Supersonic Character- Having a 450 Sweptback Wing. TN
istics of Inboard Trailing-Edge 2358, May 1951.
Flaps having Arbitrary Sweep and
Taper. Mach Lines behind Flap CONTROLS
Leading and Trailing Edges. TN (1. 2. 2. 4)
2205, October 1950.
Boddy, Lee E. and Williams, Walter C.:
Goin, Kennith L.: Equations and A Summary and Analysis of Data on
Charts for the Rapid Estimation Dive-Recovery Flaps. RM A7F09,
of Hinge-Moment and Effective- June 1947.
ness Parameters for Trailing-
Edge Controls Having Leading Phillips, William H.: Appreciation and
and Trailing Edges Swept ahead Prediction of Flying Qualities.
of the Mach Lines. TN 2221, Rept. 927, 1949.
November 1950.
DeYoung, John: Spanwise Loading for
Furlong, G. Chester and Fitzpatrick, Wings and Control Surfaces of Low
James E.: Effects of Mach Num- Aspect Ratio. TN 2011, January
ber up to 0. 34 and Reynolds 1950.
Number up to 8 x 106 on the
Maximum Lift Coefficient of a DeYoung, John: Theoretical Antisym-
Wing of NACA 66-Series Airfoil metric Span Loading for Wings of
Sections. TN 2251, December Arbitrary Plan Form at Subsonic
1950. Speeds. TN 2140, July 1950.

Dods, Jules B., Jr.: Estimation of Goin, Kennith L.: Equations and Charts
Low-Speed Lift and Hinge-Moment for the Rapid Estimation of Hinge-
Parameters for Full-Span Moment and Effectiveness Param-
Trailing-Edge Flaps on Lifting eters for Trailing-Edge Controls
Surfaces with and without Sweep- having Leading and Trailing Edges
back. TN 2288, February 1951. Swept ahead of the Mach Lines.
TN 2221, November 1950.
Slots and Slats
(1. 2. 2. 3. 2) DeYoung, John: Theoretical Symmetric
Span Loading Due to Flap Deflection
Purser, Paul E. and Spearman, for Wings of Arbitrary Plan Form
M. Leroy: Wind-Tunnel Tests at at Subsonic Speeds. TN 2278,
Low Speed of Swept and Yawed January 1951.
Wings having Various Plan Forms.
RM L7D23, May 1947. Sivells, James C. and Westrick,
Gertrude C.: Method for Calculat-
Bird, John D. and Jaquet, Byron M.: ing Lift Distributions for Unswept
A Study of the Use of Experimental Wings with Flaps or Ailerons by
Stability Derivatives in the Calcu- Use of Nonlinear Section Lift Data.
lation of the Lateral Disturbed TN 2283, January 1951.
Motions of a Swept-Wing Airplane
and Comparison with Flight Re- Flap Type
suits. TN 2013, January 1950. (1.2.2.4.1)

Queijo, M. J. and Wolhart, Walter D.: Toll, Thomas A.: Summary of Lateral-
Experimental Investigation of the Control Research. Rept. 868, 1947.
Effect of Vertical-Tail Size and
Length and of Fuselage Shape and Sawyer, Richard H.: Flight Measure-
Length on the Static Lateral Stabil- ments of the Lateral Control Char-
ity Characteristics of a Model with acteristics of Narrow-Chord Ailer-
450 Sweptback Wing and Tail Sur- ons on the Trailing Edge of a Full-
faces. TN 2168, August 1950. Span Slotted Flap. Rept. 883, 1947.







AERODYNAMICS
38 WINGS (1.2)

Flap Type Controls Complete Wings Johnson, Harold S. and Hagerman,
(Cont.) John R.: Wind-Tunnel Investigation
Purser, Paul E. and Spearman, at Low Speed of the Lateral Control
M. Leroy: Wind-Tunnel Tests at Characteristics of an Unswept Un-
Low Speed of Swept and Yawed tapered Semispan Wing of Aspect
Wings having Various Plan Forms. Ratio 3.13 Equipped with Various
RM L7D23, May 1947. 25-Percent-Chord Plain Ailerons.
TN 2199, October 1950.
Swanson, Robert S. and Crandall,
Stewart M.: Lifting-Surface- Goin, Kennith L.: Equations and Charts
Theory Aspect-Ratio Corrections for the Rapid Estimation of Hinge-
to the Lift and Hinge-Moment Moment and Effectiveness Param-
Parameters for Full-Span Ele- eters for Trailing-Edge Controls
vators on Horizontal Tail Sur- having Leading and Trailing Edges
faces. Rept. 911, 1948. Swept ahead of the Mach Lines. TN
2221, November 1950.
Tucker, Warren A. and Nelson,
Robert L.: Theoretical Character- Riebe, John M. and Watson, James M.:
istics in Supersonic Flow of Two The Effect of End Plates on Swept
Types of Control Surfaces on Tri- Wings at Low Speed. TN 2229,
angular Wings. Rept. 939, 1949. November 1950.

Dods, Jules B., Jr.: Wind-Tunnel In- Lovell, Powell M., Jr.: A Comparison
vestigation of Horizontal Tailes. of the lateral Controllability with
V 450 Swept-Back Plan Form of Flap and Plug Ailerons on a Swept-
Aspect Ratio 2. RM A9D05, back-Wing Model Having Full-Span
September 1949. Flaps. TN 2247, December 1950.

Johnson, Harold S. and Hagerman, Sivells, James C.: An Improved Ap-
John R.: Wind-Tunnel Investiga- proximate Method for Calculating
tion at Low Speed of an Unswept Lift Distributions Due to Twist.
Untapered Semispan Wing of As- TN 2282, January 1951.
pect Ratio 3.13 Equipped with
Various 25-Percent-Chord Plain Dods, Jules B., Jr.: Estimation of
Flaps. TN 2080, April 1950. Low-Speed Lift and Hinge-Moment
Parameters for Full-Span Trailing-
Carpenter, Paul J. and Paulnock, Edge Flaps on Lifting Surfaces with
Russell S.: Hovering and Low- and without Sweepback. TN 2288,
Speed Performance and Control February 1951.
Characteristics of an Aerodynamic-
Servocontrolled Helicopter Rotor Johnson, Harold S. and Hagerman,
System as Determined on the John R.: Wind-Tunnel Investigation
Langley Helicopter Tower. TN at Low Speed of Lateral Control
2086, May 1950. Characteristics of an Untapered
450 Sweptback Semispan Wing of
Lovell, Powell M., Jr. and Stassi, Aspect Ratio 1. 59 Equipped with
Paul P.: A Comparison of the Various 25-Percent-Chord Plain
Lateral Controllability with Flap Ailerons. TN 2316, March 1951.
and Plug Ailerons on a Sweptback-
Wing Model. TN 2089, May 1950. Piland, Robert 0.: Some Theoretical
Characteristics of Trapezoidal
Johnson, Harold S. and Hagerman, Wings in Supersonic Flow and a
John R.: Wind-Tunnel Investiga- Comparison of Several Wing-Flap
tion at Low Speed of a 450 Swept- Combinations. TN 2336, April
back Untapered Semispan Wing of 1951.
Aspect Ratio 1. 59 Equipped with
Various 25-Percent-Chord Plain
Flaps. TN 2169, August 1950.








AERODYNAMICS
WINGS (1.2) 39

Flap Tfpe Controls Complete .Tings Nissen, James M.; Gadeberg, Burnett L.;
(ont.) and Hamilton, William T.: Correla-
Naeseth, Rodger L. and O'Hare, tion of the Drag Characteristics of a
William M.: Effect of Aspect Ratio P-51B Airplane Obtained from High-
on the Low-Speed Lateral Control Speed Wind Tunnel and Flight Tests.
Characteristics of Unswept Un- Rept. 916, 1948.
tapered Low-Aspect-Ratio Wings.
TN 2348, May 1951. Sivells, James C. and Spooner,
Stanley H.: Investigation in the
Spoiler Langley 19-Foot Pressure Tunnel
(1. 2. 2. 4. 2) of Two Wings of NACA 65-210 and
64-210 Airfoil Sections with Various
Toll, Thomas A.: Summary of Lateral- Type Flaps. Rept. 942, 1949.
Control Research. Rept. 868,
1947. Furlong, G. Chester and Fitzpatrick,
James E.: Effects of Mach Number
Lovell, Powell M., Jr. and Stassi, up to 0.34 and Reynolds Number up
Paul P.: A Comparison of the to 8 x 106 on the Maximum Lift Co-
Lateral Controllability with Flap efficient of a Wing of NACA 66-
and Plug Ailerons on a Sweptback- Series Airfoil Sections. TN 2251,
Wing Model. TN 2089, May 1950. December 1950.

Riebe, John M. and Watson, James M.: MACH NUMBER EFFECTS
The Effect of End Plates on Swept (1. 2. 2. 6)
Wings at Low Speed. TN 2229,
November 1950. Lees, Lester: The Stability of the
Laminar Boundary Layer in a
Lovell, Powell M., Jr.: A Comparison Compressible Fluid. Rept. 876,
of the Lateral Controllability with 1947.
Flap and Plug Ailerons on a
Sweptback-Wing Model having Hamilton, William T. and Nelson,
Full-Span Flaps. TN 2247, Warren H.: Summary Report on
December 1950. the High-Speed Characteristics of
Six Model Wings having NACA
Fischel, Jack and Hagerman, John R.: 651-Series Sections. Rept. 877,
Effect of Aspect Ratio and Sweep- 1947.
back on the Low-Speed Lateral
Control Characteristics of Un- Heaslet, Max. A.; Lomax, Harvard;
tapered Low-Aspect-Ratio Wings and Jones, Arthur L.: Volterra's
Equipped with Retractable Ailerons. Solution of the Wave Equation as
TN 2347, May 1951. Applied to Three-Dimensional
Supersonic Airfoil Problems.
REYNOLDS NUMBER EFFECTS Rept. 889, 1947.
(1.2.2. 5)
Adler, Alfred A.: Effects of Combina-
Van Dyke, Milton D.: Aerodynamic tions of Aspect Ratio and Sweepback
Characteristics Including Scale at High Subsonic Mach Numbers.
Effects of Several Wings and Bodies RM L7C24, June 1947.
alone and in Combination at a Mach
Number of 1. 53. RM A6K22, Boddy, Lee E. and Williams, Walter C.:
December 1946. A Summary and Analysis of Data
on Dive-Recovery Flaps. RM
Lees, Lester: The Stability of the A7F09, June 1947.
Laminar Boundary Layer in a
Compressible Fluid. Rept. 876, Liccini, Luke L.: Effects of 450 Sweep-
1947. back on the High-Speed Character-
istics of a Wing Having a Modified
NACA 16, -12 Airfoil Section. RM
L6K18a, July 1947.







AERODYNAMICS
40 WINGS (1. 2)

Mach No. Effects Complete wings (Cont.) Diederich, Franklin W. and Zlotnick,
Martin: Theoretical Spanwise Lift
Jessen, Henry, Jr.: A Summary Report Distributions of Low-Aspect-Ratio
on the Effects of Mach Number on Wings at Speeds below and above
the Span Load Distribution on Wings the Speed of Sound. TN 1973,
of Several Models. RM A7C28, October 1949.
July 1947.
Aiken, William S., Jr. and Howard,
Brown, Clinton E. and Adams, Mac C.: Donald A.: A Comparison of Wing
Damping in Pitch and Roll of Tri- Loads Measured in Flight on a
angular Wings at Supersonic Speeds. Fighter-Type Airplane by Strain-
Rept. 892, 1948. Gage and Pressure-Distribution
Methods. TN 1967, November 1949.
Jones, Robert T. : Subsonic Flow over
Thin Oblique Airfoils at Zero Lift. Castile, George E. and Herr, Robert W.:
Rept. 902, 1948. Some Effects of Density and Mach
Number on the Flutter Speed of Two
Ribner, Herbert S. and Malvestuto, Uniform Wings. TN 1989, December
Frank S., Jr.: Stability Derivatives 1949.
of Triangular Wings at Supersonic
Speeds. Rept. 908, 1948. Cohen, Doris: Theoretical Loading at
Supersonic Speeds of Flat Swept-
Nissen, James M.; Gadeberg, Burnett L.; Back Wings with Interacting Trailing
and Hamilton, William T.: Correla- and Leading Edges. TN 1991,
tion of the Drag Characteristics of a December 1949.
P-51B Airplane Cbtained from High-
Speed Wind Tunnel and Flight Tests. Heaslet, Max. A. and Lomax, Harvard:
Rept. 916, 1948. The Calculation of Downwash behind
Supersonic Wings with an Application
Stack, John and Lindsey, W. F.: Char- to Triangular Plan Forms. Rept.
acteristics of Low-Aspect-Ratio 957, 1950.
Wings at Supercritical Mach Num-
bers. Rept. 922, 1949. Malvestuto, Frank S., Jr.; Margolis,
Kenneth; and Ribner, Herbert S.:
Harmon, Sidney M.: Stability Deriva- Theoretical Lift and Damping in Roll
tives of Thin Rectangular Wings at at Supersonic Speeds of Thin Swept-
Supersonic Speeds. Wing Diagonals back Tapered Wings with Streamwise
ahead of Tip Mach Lines. Rept. Tips, Subsonic Leading Edges and
925, 1949. Supersonic Trailing Edges. Rept.
970, 1950.
Phillips, William H.: Appreciation and
Prediction of Flying Qualities. Malvestuto, Frank S., Jr. and Margolis,
Rept. 927, 1949. Kenneth: Theoretical Stability Deriva-
tives of Thin Sweptback Wings
Tucker, Warren A. and Nelson, Tapered to a Point with Sweptback
Robert L.: Theoretical Character- or Sweptforward Trailing Edges for
istics in Supersonic Flow of Two a Limited Range of Supersonic
Types of Control Surfaces on Tri- Speeds. Rept. 971, 1950.
angular Wings. Rept. 939, 1949.
Tucker, Warren A. and Nelson, Robert L.:
Lomax, Harvard and Heaslet, Max. A.: The Effect of Torsional Flexibility
Damping-in-Roll Calculations for on the Rolling Characteristics at
Slender Swept-Back Wings and Supersonic Speeds of Tapered Un-
Slender Wing-Body Combinations. swept Wings. Rept. 972, 1950.
TN 1950, September 1949.
Mathews, Charles W. and Thompson
Ellis, Macon C., Jr. and Hasel, Jim Rogers: Comparative Drag
Lowell E.: Preliminary Investiga- Measurements at Transonic Speeds
tion at Supersonic Speeds of Tri- of Rectangular and Sweptback NACA
angular and Sweptback Wings. TN 65-009 Airfoils Mounted on a Freely
1955, October 1949. Falling Body. Rept. 988, 1950.








AERODYNAMICS
WINGS (1.2) 41

Miach No. Effects Complete :.ings (Cont.) Margolis, Kenneth: Theoretical Calcu-
lations of the Lateral Force and
Jones, Arthur L. and Alksne, Alberta: Yawing Moment Due to Rolling at
The Load Distribution Due to Side- Supersonic Speeds for Sweptback
slip on Triangular, Trapezoidal, Tapered Wings with Streamwise
and Related Plan Forms in Super- Tips. Subsonic Leading Edges.
sonic Flow. TN 2007, January TN 2122, June 1950.
1950.
Martin, John C.: The Calculation of
Kainer, Julian H.: Theoretical Calcu- Downwash behind Wings of Arbi-
lations of the Supersonic Pressure trary Plan Form at Supersonic
Distribution and Wave Drag for a Speeds. TN 2135, July 1950.
Limited Family of Tapered Swept-
back Wings with Symmetrical Para- Tucker, Warren A. and Piland, Robert 0.:
bolic-Arc Sections at Zero Lift. Estimation of the Damping in Roll of
TN 2009, January 1950. Supersonic-Leading-Edge Wing-Body
Combinations. TN 2151, July 1950.
DeYoung, John: Spanwise Loading for
Wings and Control Surfaces of Harmon, Sidney M. and Martin, John C.:
Low Aspect Ratio. TN 2011, Theoretical Calculations of the
January 1950. Lateral Force and Yawing Moment
Due to Rolling at Supersonic Speeds
Walker, Harold J. and Ballantyne, for Sweptback Tapered Wings with
Mary B.: Pressure Distribution Streamwise Tips. Supersonic Lead-
and Damping in Steady Roll at ing Edges. TN 2156, July 1950.
Supersonic Mach Numbers of Flat
Swept-Back Wings with Subsonic Walker, Harold J. and Ballantyne,
Edges. TN 2047, March 1950. Mary B.: Pressure Distribution
and Damping in Steady Pitch at
Margolis, Kenneth: Theoretical Lift Supersonic Mach Numbers of Flat
and Damping in Roll of Thin Swept- Swept-Back Wings having all Edges
back Tapered Wings with Raked-In Subsonic. TN 2197, October 1950.
and Cross-Stream Wing Tips at
Supersonic Speeds. Subsonic Czarnecki, K. R. and Mueller, James N.:
Leading Edges. TN 2048, March An Approximate Method of Calculat-
1950. ing Pressures in the Tip Region of
a Rectangular Wing of Circular-Arc
Harper, Paul W. and Flanigan, Roy E.: Section at Supersonic Speeds. TN
The Effect of Rate of Change of 2211, October 1950.
Angle of Attack on the Maximum
Lift of a Small Model. TN 2061, Furlong, G. Chester and Fitzpatrick,
March 1950. James E.: Effects of Mach Num-
ber up to 0.34 and Reynolds Num-
Cohen, Doris: Formulas and Charts ber up to 8 x 106 on the Maximum
for the Supersonic Lift and Drag Lift Coefficient of a Wing of NACA
of Flat Swept-Back Wings with 66-Series Airfoil Sections. TN
Interacting Leading and Trailing 2251, December 1950.
Edges. TN 2093, May 1950.
Carpenter, Paul J.: Effects of Con-
Harmon, Sidney M. and Jeffreys, pressibility on the Performance
Isabella: Theoretical Lift and of Two Full-Scale Helicopter
Damping in Roll of Thin Wings Rotors. TN 2277, January 1951.
with Arbitrary Sweep and Taper
at Supersonic Speeds. Supersonic Malvestuto, Frank S., Jr. and Hoover,
Leading and Trailing Edges. TN Dorothy M.: Lift and Pitching
2114, May 1950. Derivatives of Thin Sweptback
Tapered Wings with Streamwise
Barmby, J. G.; Cunningham, H. J.; Tips and Subsonic Leading Edges
and Garrick, I. E.: Study of Ef- at Supersonic Speeds. TN 2294,
fects of Sweep on the Flutter of February 1951.
Cantilever Wings. TN 2121, June
1950.







AERODYNAMICS
42 WINGS (1. 2)

Mach No. Effects Conplete ,Tings (Cont.) Haefeli, Rudolph C.; Mirels, Harold;
and Cummings, John L.: Charts
Lomax, Harvard and Sluder, Loma: for Estimating Downwash behind
Chordwise and Compressibility Rectangular, Trapezoidal, and
Corrections to Slender-Wing Triangular Wings at Supersonic
Theory. TN 2295, February 1951. Speeds. TN 2141, August 1950.

Smith, Donald W. and Heitmeyer, DeYoung, John: Theoretical Symmetric
John C. : Lift, Drag, and Pitching Span Loading Due to Flap Deflection
Moment of Low-Aspect-Ratio for Wings of Arbitrary Plan Form
Wings at Subsonic and Supersonic at Subsonic Speeds. TN 2278,
Speeds Plane Triangular Wing of January 1951.
Aspect Ratio 2 with NACA 0005-63
Section. RM A50K21, February Harmon, Sidney M.: Correspondence
1951. Flows for Wings in Linearized
Potential Fields at Subsonic and
Malvestuto, Frank S., Jr. and Hoover, Supersonic Speeds. TN 2303,
Dorothy M.: Supersonic Lift and March 1951.
Pitching Moment of Thin Sweptback
Tapered Wings Produced by Con- Michael, William H., Jr.: Analysis of
stant Vertical Acceleration. Sub- the Effects of Wing Interference on
sonic Leading Edges and Super- the Tail Contributions to the Rolling
sonic Trailing Edges. TN 2315, Derivatives. TN 2332, April 1951.
March 1951.
Harmon, Sidney M.: Method for Calcu-
Diederich, Franklin W.: A Plan-Form lating Downwash Field Due to Lifting
Parameter for Correlating Certain Surfaces at Subsonic and Supersonic
Aerodynamic Characteristics of Speeds. TN 2344, April 1951.
Swept Wings. TN 2335, April 1951.
Diederich, Franklin W.: Charts and
Piland, Robert 0.: Some Theoretical Tables for Use in Calculations of
Characteristics of Trapezoidal Downwash of Wings of Arbitrary
Wings in Supersonic Flow and a Plan Form. TN 2353, May 1951.
Comparison of Several Wing-Flap
Combinations. TN 2336, April BOUNDARY LAYER
1951. (1.2.2.8)

WAKE Stuper: Flight Experiences and Tests on
(1.2.2.7) Two Airplanes with Suction Slots.
TM 1232, January 1950.
Heaslet, Max. A. and Lomax, Harvard:
The Calculation of Downwash be- Vincenti, Walter G.: Comparison be-
hind Supersonic Wings with an tween Theory and Experiment for
Application to Triangular Plan Wings at Supersonic Speeds. TN
Forms. Rept. 957, 1950. 2100, June 1950.

Mirels, Harold and Haefeli, Rudolph C.: Horton, Elmer A.; Loftin, Laurence K.,
Line-Vortex Theory for Calcula- Jr.; and Racisz, Stanley F.:
tion of Supersonic Downwash. Analysis of the Effects of Boundary-
Rept. 983, 1950. Layer Control on the Power-Off
Landing Performance Characteris-
Martin, John C.: The Calculation of tics of a Liaison Type of Airplane.
Downwash behind Wings of Arbi- TN 2143, August 1950.
trary Plan Form at Supersonic
Speeds. TN 2135, July 1950. Moore, Franklin K.: Three-Dimensional
Compressible Laminar Boundary-
Layer Flow. TN 2279, March 1951.








AERODYNAMICS
WINGS (1.2) 43

Boundary Layer Complete Jlinps (Cont.)

Mager, Artur: Generalization of
Boundary-Layer Momentum-
Integral Equations to Three-
Dimensional Flows Including
Those of Rotating System. TN
2310, March 1951.







44 AERODYNAMICS






Bodies

(1.3)


Soule, Harold V. and Sabol, Alexander P.: Cooper, Morton and Webster, Robert A.:
Development and Preliminary Inves- The Use of an Uncalibrated Cone for
tigation of a Method of Obtaining Determination of Flow Angles and
Hypersonic Aerodynamic Data by Mach Numbers at Supersonic Speeds.
Firing Models through Highly TN 2190, March 1951.
Cooled Gases. TN 2120, July 1950.

Chapman, Dean R.: An Analysis of Base SHAPE VARIABLES
Pressure at Supersonic Velocities 3.2 \
and Comparison with Experiment. ( )
TN 2137, July 1950.
Chapman, Dean R. and Perkins,
Edward W.: Experimental Investi-
THEORY gation of the Effects of Viscosity on
the Drag of Bodies of Revolution at
(1.3.1) at Mach Number of 1.5. RM
A7A31a, April 1947.
Spreiter, John R. : The Aerodynamic
Forces on Slender Plane- and Jack, John R.: Theoretical Wave Drags
Cruciform-Wing and Body Combi- and Pressure Distributions for
nations. Rept. 962, 1950. Axially Symmetric Open-Nose Bodies.
TN 2115, June 1950.
Allen, H. Julian: Pressure Distribution
and Some Effects of Viscosity on Wimbrow, William R. and Scherrer,
Slender Inclined Bodies of Revolu- Richard: Laminar-Boundary-Layer
tion. TN 2044, March 1950. Heat-Transfer Characteristics of a
Body of Revolution with a Pressure
Moore, Franklin: Linearized Super- Gradient at Supersonic Speeds. TN
sonic Axially Symmetric Flow 2148, August 1950.
about Open-Nosed Bodies Obtained
by Use of Stream Function. TN FINENESS RATIO
2116, June 1950. (1.3.2.1)

Ferri, Antonio: Supersonic Flow Chapman, Dean R. and Perkins,
around Circular Cones at Angles Edward W.: Experimental Investi-
of Attack. TN 2236, November gation of the Effects of Viscosity on
1950. the Drag of Bodies of Revolution at
a Mach Number of 1. 5. RM
Ehret, Dorris M.; Rossow, Vernon J.; A7A31a, April 1947.
and Stevens, Victor I.: An Analysis
of the Applicability of the Hypersonic Matthews, Clarence W.: A Comparison
Similarity Law to the Study of Flow of the Experimental Subsonic Pres-
about Bodies of Revolution at Zero sure Distributions about Several
Angle of Attack. TN 2250, Decem- Bodies of Revolution with Pressure
ber 1950. Distributions Computed by Means
of the Linearized Theory. RM
Van Dyke, Milton D.: A Study of L9F28, September 1949.
Second-Order Supersonic-Flow
Theory. TN 2200, January 1951.








AERODYNAMICS
BODIES (1.3) 45

Fineness Ratio Shape Variables (Cont.) Wimbrow, William R.: Experimental In-
vestigation of Temperature Recovery
Queijo, M. J. and Wolhart, Walter D.: Factors on Bodies of Revolution at
Experimental Investigation of the Supersonic Speeds. TN 1975, Oc-
Effect of Vertical-Tail Size and tober 1949.
Length and of Fuselage Shape and
Length on the Static Lateral Stabil- Jack, John R.: Theoretical Wave Drags
ity Characteristics of a Model with and Pressure Distributions for Axi-
450 Sweptback Wing and Tail Sur- ally Symmetric Open-Nose Bodies.
faces. TN 2168, August 1950. TN 2115, June 1950.

Ehret, Dorris M.; Rossow, Vernon J.; Tillmann, W.: Additional Measurements
and Stevens, Victor I.: An Analy- of the Drag of Surface Irregularities
sis of the Applicability of the Hyper- in Turbulent Boundary Layers. TM
sonic Similarity Law to the Study of 1299, January 1951.
Flow about Bodies of Revolution at
Zero Angle of Attack. TN 2250, Gowan, William H., Jr. and Mulholland,
December 1950. Donald R. : Effectiveness of Thermal-
Pneumatic Airfoil-Ice-Protection
Letko, William: Effect of Vertical-Tail System. RM E50K10a, April 1951.
Area and Length on the Yawing
Stability Characteristics of a Model
having a. 450 Sweptback Wing. TN CANOPIES
2358, May 1951. (.3.3
(1.3.3)
THICKNESS DISTRIBUTION
(1.3.2.3) Huston, Wilber B. and Skopinski, T, H.:
Flight Investigation of the Pressure
Van Dyke, Milton D.: Aerodynamic Distributions and Loads on a Front
Characteristics Including Scale and Rear Sliding Canopy. RM
Effects of Several Wings and L50B03, April 1950.
Bodies alone and in Combination
at a Mach Number of 1. 53. RM
A6K22, December 1946. DUCTED BODIES

Queijo, M. J. and Wolhart, Walter D.: (1.3.4)
Experimental Investigation of the
Effect of Vertical-Tail Size and Moore, Franklin: Linearized Supersonic
Length and of Fuselage Shape and Axially Symmetric Flow about Open-
Length on the Static Lateral Stabil- Nosed Bodies Obtained by Use of
ity Characteristics of a Model with Stream Function. TN 2116, June
450 Sweptback Wing and Tail Sur- 1950.
faces. TN 2168, August 1950.
NOSE SHAPE
SURFACE CONDITIONS (1.3.4.1)
(1. 3. 2.4)
Nichols, Mark R. and Keith, Arvid L., Jr.:
Van Dyke, Milton D.: Aerodynamic Investigation of a Systematic Group
Characteristics Including Scale Ef- of NACA 1-Series Cowlings with and
fects of Several Wings and Bodies without Spinners. Rept. 950, 1949.
alone and in Combination at a Mach
Number of 1. 53. RM A6K22, De- Bridel, Walter: Theory of Plane, Sym-
cember 1946. metrical Inlet Diffusers. TM 1267,
April 1950.
Chapman, Dean R. and Perkins,
Edward W.: Experimental Investi- Ferri, Antonio and Nucci, Louis M.:
gation of the Effects of Viscosity on Preliminary Investigation of a New
the Drag of Bodies of Revolution at Type of Supersonic Inlet. TN 2286,
a Mach Number of 1. 5. RM A7A31a, April 1951.
April 1947.






46 AERODYNAMICS






Internal Aerodynamics

(1.4)


Goldstein, Arthur W.: Analysis of the Nichols, Mark R. and Keith, Arvid L., Jr.:
Performance of a Jet Engine from Investigation of a Systematic Group of
Characteristics of the Components. NACA 1-Series Cowlings with and
I Aerodynamic and Matching Char- without Spinners. Rept. 950, 1949.
acteristics of the Turbine Compo-
nent Determined with Cold Air. Birdel, Walter: Theory of Plane, Sym-
Rept. 878, 1947. metrical Inlet Diffusers. TM 1267,
April 1950.
Sinnette, John T., Jr.: Some Methods
of Analyzing the Effect of Basic Subsonic
Design Variables on Axial-Flow (1.4.1. 1. 2)
Compressor Performance. Rept.
901, 1948. Schubauer, G. B. and Spangenberg, W. G.:
Effect of Screens in Wide-Angle Dif-
Wu, Chung-Hua: Survey of Available fusers. Rept. 949, 1949.
Information on Internal Flow Losses
through Axial Turbomachines. RM Supersonic
E50J13, January 1951. (1.4. 1.1. 3)

Henry, John R. and Bennett, J. Buel: Schubauer, G. B. and Spangenberg, W. G.:
Method for Calculation of Ram-Jet Effect of Screens in Wide-Angle Dif-
Performance. TN 2357, June 1951. fusers. Rept. 949, 1949.

Ferri, Antonio and Nucci, Louis M.:
INLETS Preliminary Investigation of aNew
Type of Supersonic Inlet. TN 2286,
(1.4.1) April 1951.

Martin, Norman J. and Holzhauser, Jack, John R.: Theoretical Wave Drags
Curt A.: Analysis of Factors In- and Pressure Distributions for
fluencing the Stability Character- Axially Symmetric Open-Nose Bodies.
istics of Symmetrical Twin-Intake TN 2115, June 1950.
Air-Induction Systems. TN 2049,
March 1950. ANNULAR
(1.4.1.2)
Ruden, P.: Two-Dimensional Sym-
metrical Inlets with External Nichols, Mark R. and Keith, Arvid L., Jr.:
Compression. TM 1279, March Investigation of a Systematic Group of
1950. NACA 1-Series Cowlings with and
without Spinners. Rept. 950, 1949.
CENTRAL
(1.4.1.1) Ferri, Antonio and Nucci, Louis M.:
Preliminary Investigation of a New
Baals, Donald D.; Smith, Norman F.; Type of Supersonic Inlet. TN 2286,
and Wright, John B.: The Develop- April 1951.
ment and Application of High-
Critical-Speed Nose Inlets. Rept.
920, 1948.








AERODYNAMICS
INTERNAL (1.4) 47

LEADING EDGE Schifer, Manfred and Tollmien, W.:
(1.4.1.3) Rotationally Symmetric Potential
Flows. TM 1244, November 1949.
Ruden, P.: Two-Dimensional Symmet-
rical Inlets with External Compres- Wu, Chung-Hua: General Through-Flow
sion. TM 1279, March 1950. Theory of Fluid Flow with Subsonic
or Supersonic Velocity in Turbo-
Br6del, Walter: Theory of Plane, Sym- machines of Arbitrary Hub and
metrical Inlet Diffusers. TM 1267, Casing Shapes. TN 2302, March
April 1950. 1951.

SIDE Subsonic
(1.4.1.4) (1.4. 2. 1.1)

Ruden, P.: Two-Dimensional Symmet- Schubauer, G. B. and Spangenberg,
rical Inlets with External Compres- W. G.: Effect of Screens in Wide-
sion. TM 1279, March 1950. Angle Diffusers. Rept. 949, 1949.

Scoops Cohen, C. B. and Valerino, A. S.: In-
(1.4.1.4.1) vestigation of Operating Pressure
Ratio of a Supersonic Wind Tunnel
Ruden, P.: Two-Dimensional Symmet- Utilizing Distributed Boundary-
rical Inlets with External Compres- Layer Suction in Test Section.
sion. TM 1279, March 1950. RM E50H04, November 1950.

Supersonic
DUCTS (1.4.2.1.2)

(1.4.2) Schubauer, G. B. and Spangenberg, W. G.:
Effect of Screens in Wide-Angle
Perl, W. and Moses, H. E.: Velocity Diffusers. Rept. 949, 1949.
Distribution on Two-Dimensional
Wing-Duct Inlets by Conformal Cohen, C. B. and Valerino, A. S.: In-
Mapping. Rept. 893, 1948. vestigation of Operating Pressure
Ratio of a Supersonic Wind Tunnel
Martin, Norman J. and Holzhauser, Utilizing Distributed Boundary-
Curt A.: Analysis of Factors In- Layer Suction in Test Section.
fluencing the Stability Character- RM E50H04, November 1950.
istics of Symmetrical Twin-Intake
Air-Induction Systems. TN 2049, Ferri, Antonio and Nucci, Louis M.:
March 1950. Preliminary Investigation of a New
Type of Supersonic Inlet. TN
Laufer, John: Investigation of Turbu- 2286, April 1951.
lent Flow in a Two-Dimensional
Channel. TN 2123, July 1950. NOZZLES
(1.4.2.2)
DIFFUSERS
(1.4.2.1) Pinkel, I. Irving: Equations for the De-
sign of Two-Dimensional Supersonic
Wright, Linwood C.: Investigation to Nozzles. Rept. 907, 1948.
Determine Contraction Ratio for
Supersonic-Compressor Rotor. Grey, Ralph E., Jr. and Wilsted, H. Dean:
RM E7L23, April 1948. Performance of Conical Jet Nozzles
in Terms of Flow and Velocity Co-
Schubauer, G. B. and Spangenberg, W. G.: efficients. Rept. 933, 1949.
Effect of Screens in Wide-Angle
Diffusers. Rept. 949, 1949. Schubauer, G. B. and Spangenberg, W. G.:
Sffect of Screens in Wide-Angle
Diffusers. Rept. 949, 1949.







AERODYNAMICS
48 INTERNAL (1.4)

Nozzles Ducts (Cont.) Nikuradse, J.: Laws of Flow in Rough
Pipes. TM 1292, November 1950.
Sanders, John C. and Brightwell,
Virginia L.: Analysis of Ejector Desmon, Leland G. and Sams, Eldon W.:
Thrust by Integration of Calculated Correlation of Forced-Convection
Surface Pressures. TN 1958, Heat-Transfer Data for Air Flowing
October 1949. in Smooth Platinum Tube with Long-
Approach Entrance at High Surface
Falkovich, S. V.: A Class of de Laval and Inlet-Air Temperatures. RM
Nozzles. TM 1236, October 1949. E50H23, November 1950.

Schiifer, Manfred and Tollmien, W.: BENDS
Rotationally Symmetric Potential (1.4.2.4)
Flows. TM 1244, November 1949.
Mager, Artur: Generalization of Boundary-
Roy, Maurice: Theoretical Investiga- Layer Momentum-Integral Equations
tions on the Efficiency and the to Three-Dimensional Flows Includ-
Conditions for the Realization of ing Those of Rotating System. TN
Jet Engines. TM 1259, June 1950. 2310, March 1951.

Lindsey, Walter F. and Chew, William L.:
The Development and Performance EXITS
of Two Small Tunnels Capable of
Intermittent Operation at Mach (1.4.3)
Numbers between 0. 4 and 4. 0.
TN 2189, September 1950. Corrsin, Stanley and Uberoi, Mahinder S.:
Spectrums and Diffusion in a Round
Spooner, Robert B.: Effect of Heat- Turbulent Jet. TN 2124, July 1950.
Capacity Lag on a Variety of
Turbine-Nozzle Flow Processes.
TN 2193, October 1950. CASCADES

Brinich, Paul F.: Boundary-Layer (1.4.5)
Measurements in 3.84- by 10-Inch
Supersonic Channel. TN 2203, Katzoff, S.; Finn, Robert S.; and
October 1950. Laurence, James C.: Interference
Method for Obtaining the Potential
Wu, Chung-Hua: General Through-Flow Flow past an Arbitrary Cascade of
Theory of Fluid Flow with Subsonic Airfoils. Rept. 879, 1947.
or Supersonic Velocity in Turbo-
machines of Arbitrary Hub and Spurr, Robert A. and Alien, H. Julian:
Casing Shapes. TN 2302, March A Theory of Unstaggered Airfoil
1951. Cascades in Compressible Flow.
Rept. 888, 1947.
PIPES
(1.4.2.3) Finger, Harold B.; Schum, Harold J.;
and Buckner, Howard A., Jr.: In-
Lowdermilk, Warren H. and Grele, vestigation of Inlet Guide Vanes for
Milton D.: Influence of Tube- a Multistage Axial-Flow Compres-
Entrance Configuration on Average sor. TN 1954, October 1949.
Heat-Transfer Coefficients and
Friction Factors for Air Flowing Goldstein, Arthur W. and Mager, Artur:
in an Inconel Tube. RM E50E23, Attainable Circulation of Airfoils in
August 1950. Cascade. Rept. 953, 1950.

Kaufman, Samuel J. and Isely, Francis D.: Costello, George R.: Method of Design-
Preliminary Investigation of Heat ing Cascade Blades with Prescribed
Transfer to Water Flowing in an Velocity Distributions in Compres-
Electrically Heated Inconel Tube. sible Potential Flows. Rept. 978,
RM E50G31, September 1950. 1950.







AERODYNAMICS
INTERNAL (1.4) 49

Cascades (Cont.) Bugaenko, G A.: On the Problem of Gas
Flow over an Infinite Cascade Using
Corrsin, Stanley and Uberoi, Mahinder S.: Chaplygin's Approximation. TM
Further Experiments on the Flow and 1298, May 1951.
Heat Transfer in a Heated Turbulent
Air Jet. Rept. 998, 1950. EXPERIMENT
(1.4. 5.2)
Wu, Chung-Hua: Formulas and Tables of
Coefficients for Numerical Differen- Hauser, Cavour H.; Plohr, Henry W.;
tiations with Function Values Given and Sonder, Gerhard: Study of Flow
at Unequally Spaced Points and Ap- Conditions and Deflection Angle at
plication to Solution of Partial Dif- Exit of Two-Dimensional Cascade of
ferential Equations. TN 2214, Turbine Rotor Blades at Critical and
November 1950. Supercritical Pressure Ratios. RM
E9K25, March 1950.
Savage, Melvyn and Westphal, Willard R.:
Analysis of the Effects of Design Lieblein, Seymour: Turning-Angle Design
Pressure Ratio per Stage and Off- Rules for Constant-Thickness Circular-
Design Efficiency on the Operating Arc Inlet Guide Vanes in Axial Annular
Range of Multistage Axial-Flow Flow. TN 2179, September 1950.
Compressors. TN 2248, December
1950. FANS
Wu, Chung-Hua: Survey of Available In-
formation on Internal Flow Losses ,1 4.6
through Axial Turbomachines. RM
E50J13, January 1951. Oergel, C. T. and Foote, W. R.: Report
on Jet Propulsion. ACR, August 1941.
THEORY
(1.4.5.1) Acker, Loren W. and Klienknecht,
Kenneth S.: Flight Comparison of
Westphal, Willard R. and Dunavant, Performance and Cooling Character-
James C.: Application of the Wire- istics of Exhaust-Ejector Installation
Mesh Plotting Device to Incompres- with Exhaust-Collector-Ring Installa-
sible Cascade Flows. TN 2095, tion. RM E6L13a, February 1947.
May 1950.
Sanders, John C. and Brightwell,
Hansen, Arthur G. and Yohner, Peggy L.: Virginia L.: Analysis of Ejector
A Numerical Procedure for Design- Thrust by Integration of Calculated
ing Cascade Blades with Prescribed Surface Pressures. TN 1958,
Velocity Distribution in Incompres- October 1949.
sible Flow. TN 2101, June 1950.
Reid, Elliott G.: Annular-Jet Ejectors.
Lieblein, Seymour and Sandercock, TN 1949, November 1949.
Donald M.: Compressibility Cor-
rection for Turning Angles of Axial- Boxer, Emanuel: Influence of Wall
Flow Inlet Guide Vanes. TN 2215, Boundary Layer upon the Perform-
December 1950. ance of an Axial-Flow Fan Rotor.
TN 2291, February 1951.
Costello, George R.; Cummings,
Robert L.; and Sinnette, John T., Jr.:
Detailed Computational Procedure
for Design of Cascade Blades with
Prescribed Velocity Distributions
in Compressible Potential Flows.
TN 2281, February 1951.







AERODYNAMICS
50 INTERNAL (1.4)


BOUNDARY LAYER

(1.4.7) Cohen, C. B. and Valerino, A. S.:
Investigation of Operating Pressure
Sinnette, John T., Jr.: Some Methods Ratio of a Supersonic Wind Tunnel
of Analyzing the Effect of Basic De- Utilizing Distributed Boundary-
sign Variables on Axial-FlowCom- Layer Suction in Test Section. RM
pressor Performance. Rept. 901, E50H04, November 1950.
1948.
Wu, Chung-Hua: Survey of Available In-
Wright, Linwood C.: Investigation to formation on Internal Flow Losses
Determine Contraction Ratio for through Axial Turbomachines. RM
Supersonic-Compressor Rotor. E50J13, January 1951.
RM E7L23, April 1948.
Boxer, Emanuel: Influence of Wall
Ritter, William K. and Johnsen, Boundary Layer upon the Perform-
Irving A.: Performance of 24-Inch ance of an Axial-Flow Fan Rotor.
Supersonic Axial-Flow Compressor TN 2291, February 1951.
in Air. I Performance of Com-
pressor Rotor at Design Tip Speed Mager, Artur: Generalization of Boundary-
of 1600 Feet per Second. RM Layer Momentum-Integral Equations
E7L10, May 1948. to Three-Dimensional Flows Including
those of Rotating System. TN 2310,
Donaldson, Coleman duP. and Sullivan, March 1951.
Roger D.: The Effect of Wall Fric-
tion on the Strength of Shock Waves Liepmann, H. W.; Roshko, A.; and
in Tubes and Hydraulic Jumps in Dhawan, S.: On Reflection of Shock
Channels. TN 1942, September Waves from Boundary Layers. TN
1949. 2334, April 1951.

Goldstein, Arthur W. and Mager, Artur: Tucker, Maurice: Approximate Calcula-
Attainable Circulation of Airfoils tion of Turbulent Boundary-Layer
in Cascade. Rept. 953, 1950. Development in Compressible Flow.
TN 2337, April 1951.
Wu, Chung-Hua and Wolfenstein, Lincoln:
Application of Radial-Equilibrium BOUNDARY LAYER CHARACTERISTICS
Condition to Axial-Flow Compressor (1.4.7.1)
and Turbine Design. Rept. 955,
1950. Wright, Linwood C.: Investigation to De-
termine Contraction Ratio for Super-
Tucker, Maurice: Approximate Turbu- sonic-Compressor Rotor. RM
lent Boundary-Layer Development E7L23, April 1948.
in Plane Compressible Flow along
Thermally Insulated Surfaces with Costello, George R.: Method of Design-
Application to Supersonic-Tunnel ing Blades with Prescribed Velocity
Contour Correction. TN 2045, Distributions in Compressible
March 1950. Potential Flows. Rept. 978, 1950.

Laufer, John: Investigation of Turbulent Finger, Harold B.: Method of Experi-
Flow in a Two-Dimensional Channel. mentally Determining Radial Distri-
TN 2123, July 1950. butions of Velocity through Axial-
Flow Compressor. TN 2059, April
Brinich, Paul F.: Boundary-Layer 1950.
Measurements in 3. 84- by 10-Inch
Supersonic Channel. TN 2203, Liepmann, H. W.; Roshko, A.; and
October 1950. Dhawan, S.: On Reflection of Shock
Waves from Boundary Layers. TN
2334, April 1951.







AERODYNAMICS
INTERNAL (1.4) 51

BOUNDARY-LAYER CONTROL
(1.4.7.2)

Sinnette, John T., Jr. and Costello,
George R.: Possible Application
of Blade Boundary-Layer Control
to Improvement of Design and Off-
Design Performance of Axial-Flow
Turbomachines. TN 2371, May
1951.







52 AERODYNAMICS





Propellers

(1.5)


Hubbard, Harvey I. : Sound Measure- Hubbard, Harvey H. and Lassiter,
ments for Five Shrouded Propellers Leslie W.: Sound from a Two-Blade
at Static Conditions. TN 2024, April Propeller at Supersonic Tip Speeds.
1950. RM L51C27, May 1951.

Bird, John D. and Jaquet, Byron M.: A
Study of the Use of Experimental DESIGN VARIABLES
Stability Derivatives in the Calcula- (1.2)
tion of the Lateral Disturbed Mo- 1.5.2
tions of a Swept-Wing Airplane and
Comparison with Flight Results. Baker, John E. and Paulnock, Russell S.:
TN 2013, January 1950. Experimental Investigation of Flutter
of a Propeller with Clark Y Section
Operating at Zero Forward Velocity
THEORY at Positive and Negative Blade-Angle
(1.5.1) Settings. TN 1966, December 1949.
Hubbard, Harvey H.: Sound Measurements
Crigler, John L.: Application of for Five Shrouded Propellers at Static
Theodorsen's Theory to Propeller Conditions. TN 2024, April 1950.
Design. Rept. 924, 1949.
Beranek, Leo L.; Elwell, Fred S.;
Hubbard, Harvey H. and Regier, Roberts, John P.; and Taylor,
Arthur A.: Free-Space Oscillating C. Fayette: Experiments in External
Pressures near the Tips of Rotat- Noise Reduction of Light Airplanes.
ing Propellers. Rept. 996, 1950. TN 2079, May 1950.

Vogeley, Arthur W.: Axial-Momentum BLADE SECTIONS
Theory for Propellers in Compres- (1.5.2.1)
sible Flow. TN 2164, August 1950.
Delano, James B.: Investigation of Two-
Roberts, John C. and Yaggy, Paul F.: Blade Propellers at High Forward
A Survey of the Flow at the Plane Speeds in the NACA 8-Foot High-
of the Propeller of a Twin-Engine Speed Tunnel. III Effects of
Airplane. TN 2192, September Camber and Compressibility NACA
1950. 4-(5)(08)-03 and NACA 4-(10)(08)-03
Blades. ACR L5F15, August 1945.
Rogallo, Vernon L.; Roberts, John C.;
and Oldaker, Merritt R.: Vibra- Evans, Albert J. and Klunker,
tory Stresses in Propellers Operat- E. Bernard: Preliminary Investiga-
ing in the Flow Field of a Wing- tion of Two Full-Scale Propellers to
Nacelle-Fuselage Combination. Determine the Effect of Swept-Back
TN 2308, March 1951. Blade Tips on Propeller Aerodynamic
Characteristics. RM L6J21, May
Mager, Artur: Generalization of 1947.
Boundary-Layer Momentum-
Integral Equations to Three- Gendler, Sel and Johnson, Donald F.:
Dimensional Flows Including Determination of Minimum Moments
those of Rotating System. TN of Inertia of Arbitrarily Shaped Areas,
2310, March 1951. Such as Hollow Turbine Blades. RM
E9H10, February 1950.








AERODYNAMICS
PROPELLERS (1. 5) 53

Blade Sections Design Variables (Cont.) MACH NUMBER EFFECTS
(1. 5.2. 5)
Vogeley, Arthur W.: Axial-Momentum
Theory for Propellers in Compres- Delano, James B.: Investigation of Two-
sible Flow. TN 2164, August 1950. Blade Propellers at High Forward
Speeds in the NACA 8-Foot High-
Delano, James B. and Carmel, Speed Tunnel. III Effects of
Melvin M.: Tests of Two-Blade Camber and Compressibility NACA
Propellers in the Langley 8-Foot 4-(5)(03)-03 and NACA 4-(10)(08)-03
High-Speed Tunnel to Determine Blades. ACR L5F15, August 1945.
the Effect on Propeller Perform-
ance of a Modification of Inboard Evans, Albert J. and Klunker,
Pitch Distribution. TN 2268, E. Bernard: Preliminary Investiga-
February 1951. tion of Two Full-Scale Propellers to
Determine the Effect of Swept-Back
SOLIDITY Blade Tips on Propeller Aerodynamic
(1.5.2.2) Characteristics. RM L6J21, May
1947.
Vogeley, A. W.: Sound-Level Measure-
ments of a Light Airplane Modified Hubbard, Harvey H. and Regier, Arthur A.:
to Reduce Noise Reaching the Free-Space Oscillating Pressures
Ground. Rept. 926, 1949. near the Tips of Rotating Propellers.
Rept. 996, 1950.
Stack, John; Draley, Eugene C.; Delano,
James B.; and Feldman, Lewis: Stack, John; Draley, Eugene C.; Delano,
Investigation of the NACA 4-(3)(08)- James B.; and Feldman, Lewis:
03 and NACA 4-(3)(08)-045 Two- Investigation of the NACA 4-(3)(08)-
Blade Propellers at Forward Mach 03 and NACA 4-(3)(08)-045 Two-
Numbers to 0. 725 to Determine the Blade Propellers at Forward Mach
Effects of Compressibility and Numbers to 0. 725 to Determine the
Solidity on Performance. Rept. Effects of Compressibility and
999, 1950. Solidity on Performance. Rept. 999,
1950.
PITCH DISTRIBUTION
(1.5.2.3) Hammack, Jerome B. and Vogeley, A. W.:
Propeller Flight Investigation to
Delano, James B. and Carmel, Determine the Effects of Blade Load-
Melvin M.: Tests of Two-Blade ing. TN 2022, January 1950.
Propellers in the Langley 8-Foot
High-Speed Tunnel to Determine Vogeley, Arthur W.: Axial-Momentum
the Effect on Propeller Perform- Theory for Propellers in Compres-
ance of a Modification of Inboard sible Flow. TN 2164, August 1950.
Pitch Distribution. TN 2268,
February 1951. Delano, James B. and Carmel, Melvin M.:
Tests of Two-Blade Propellers in the
BLADE PLANFORMS Langley 8-Foot High-Speed Tunnel
(1. 5. 2. 4) to Determine the Effect on Propeller
Performance of a Modification of
Evans, Albert J. and Klunker, E. Inboard Pitch Distribution. TN
Bernard: Preliminary Investigation 2268, February 1951.
of Two Full-Scale Propellers to
Determine the Effect of Swept-Back Hubbard, Harvey H. and Lassiter,
Blade Tips on Propeller Aerody- Leslie W.: Sound from a Two-
namic Characteristics. RM L6J21, Blade Propeller at Supersonic
May 1947. Tip Speeds. RM L51C27, May
1951
Hubbard, Harvey H. and Regier,
Arthur A.: Free-Space Oscillating
Pressures near the Tips of Rotat-
ing Propellers. Rept. 996, 1950.







AERODYNAMICS
54 PROPELLERS (1.5)

PUSHER Weil, Joseph, and Sleeman, William G., Jr.:
(1.5.2.6) Prediction of the Effects of Propel-
ler Operation on the Static Longi-
Schade, Robert 0.: Free-Flight-Tunnel tudinal Stability of Single-Engine
Investigation of Dynamic Longitudi- Tractor Monoplanes with Flaps Re-
nal Stability as Influenced by the tracted. Rept. 941, 1949.
Static Stability Measured in Wind-
Tunnel Force Tests under Condi- Roberts, John C. and Yaggy, Paul F.:
tions of Constant Thrust and A Survey of the Flow at the Plane
Constant Power. TN 2075, April of the Propeller of a Twin-Engine
1950. Airplane. TN 2192, September
1950.
DUAL ROTATION
(1.5.2.7) Rogallo, Vernon L.; Roberts, John C.;
and Oldaker, Merritt R. : Vibratory
Crigler, John L.: Application of Stresses in Propellers Operating in
Theodorsen's Theory to Propeller the Flow Field of a Wing-Nacelle-
Design. Rept. 924, 1949. Fuselage Combination. TN 2308,
March 1951.
INTERFERENCE OF BODIES
(1. 5. 2. 8) DIAMETER
(1. 5. 2. 10)
Weil, Joseph and Sleeman, William G., Jr.:
Prediction of the Effects of Propel- Weil, Joseph and Sleeman, William G., Jr.:
ler Operation on the Static Longi- Prediction of the Effects of Propeller
tudinal Stability of Single-Engine Operation on the Static Longitudinal
Tractor Monoplanes with Flaps Stability of Single-Engine Tractor
Retracted. Rept. 941, 1949. Monoplanes with Flaps Retracted.
Rept. 941, 1949.
Hubbard, Harvey H. and Regier,
Arthur A.: Free-Space Oscillating
Pressures near the Tips of Rotating DESIGNATED TYPES
Propellers. Rept. 996, 1950. (
(1.5.3)
Vogeley, Arthur W.: Axial-Momentum
Theory for Propellers in Compres- Delano, James B. : Investigation of Two-
sible Flow. TN 2164, August 1950. Blade Propellers at High Forward
Speeds in the NACA 8-Foot High-
Roberts, John C. and Yaggy, Paul F.: Speed Tunnel. III Effects of
A Survey of the Flow at the Plane Camber and Compressibility NACA
of the Propeller of a Twin-Engine 4-(5)(0C)-03 and NACA 4-(10)(08)-03
Airplane. TN 2192, September Blades. ACR L5F15, August 1945.
1950.
Stack, John; Draley, Eugene C.; Delano,
Rogallo, Vernon L.; Roberts, John C.; James B.; and Feldman, Lewis:
and Oldaker, Merritt R. : Vibra- Investigation of the NACA 4-(3)(08)-03
tory Stresses in Propellers Operat- and NACA 4-(3)(08)-045 Two-Blade
ing in the Flow Field of a Wing- Propellers at Forward Mach Num-
Nacelle-Fuselage Combination. bers to 0. 725 to Determine the Ef-
TN 2308, March 1951. fects of Compressibility and Solidity
on Performance. Rept. 999, 1950.
PITCH AND YAW
(1.5.2.9) Roy, Maurice: Theoretical Investigations
on the Efficiency and the Conditions
Phillips, William H.: Appreciation and for the Realization of Jet Engines.
Prediction of Flying Qualities. TM 1259, June 1950.
Rept. 927, 1949.








AERODYNAMICS
PROPELLERS (1.5) 55

Designated Tymes (Cont.) Well, Joseph and Sleeman,
William G., Jr.: Prediction of the
Delano, James B. and Carmel, Effects of Propeller Operation on
Melvin M.: Tests of Two-Blade the Static Longitudinal Stability of
Propellers in the Langley 8-Foot Single-Engine Tractor Monoplanes
High-Speed Tunnel to Determine with Flaps Retracted. Rept. 941,
the Effect on Propeller Perform- 1949.
ance of a Modification of Inboard
Pitch Distribution. TN 2268, Baker, John E. and Paulnock, Russell S.:
February 1951. Experimental Investigation of Flutter
of a Propeller with Clark Y Section
Operating at Zero Forward Velocity
at Positive and Negative Blade-Angle
SLIPSTREAM Settings. TN 1966, December 1949.
S\ Hammack, Jerome B. and Vogeley, A. W.:
(1 5.4) Propeller Flight Investigation to
Determine the Effects of Blade Load-
Weil, Joseph and Sleeman, ing. TN 2022, January 1950.
William G., Jr.: Prediction of
the Effects of Propeller Opera- Lange, Roy H. and McLemore, Huel C.:
tion on the Static Longitudinal Static Longitudinal Stability and
Stability of Single-Engine Tractor Control of a Convertible-Type Air-
Monoplanes with Flaps Retracted. plane as Affected by Articulated-
Rept. 941, 1949. and Rigid-Propeller Operation. TN
2014, February 1950.
Lange, Roy H. and McLemore, Huel C.:
Static Longitudinal Stability and Neel, Carr B., Jr. and Bright, Loren G.:
Control of a Convertible-Type The Effect of Ice Formations on Pro-
Airplane as Affected by Articulated- peller Performance. TN 2212,
and Rigid-Propeller Operation. October 1950.
TN 2014, February 1950.
Delano, James B. and Carmel,
Vogeley, Arthur W.: Axial-Momentum Melvin M.: Tests of Two-Blade
Theory for Propellers in Compres- Propellers in the Langley 8-Foot
sible Flow. TN 2164, August 1950. High-Speed Tunnel to Determine
the Effect on Propeller Perform-
Delano, James B. and Carmel, ance of a Modification of Inboard
Melvin M.: Tests of Two-Blade Pitch Distribution. TN 2268,
Propellers in the Langley 8-Foot February 1951.
High-Speed Tunnel to Determine
the Effect on Propeller Perform- Rogallo, Vernon L; Roberts, John C.;
ance of a Modification of Inboard and Oldaker, Merritt R.: Vibratory
Pitch Distribution. TN 2268, Stresses in Propellers Operating in
February 1951. the Flow Field of a Wing-Nacelle-
Fuselage Combination. TN 2308,
March 1951.
OPERATING CONDITIONS

(1.5.6)

Vogeley, A. W.: Sound-Level Mea-
surements of a Light Airplane
Modified to Reduce Noise Reach-
ing the Ground. Rept. 926, 1949.

Phillips, William H.: Appreciation and
Prediction of Flying Qualities.
Rept. 927, 1949.







56 AERODYNAMICS





Rotating Wings

(1.6)


Carpenter, Paul J. and Paulnock, Amer, Kenneth B. and Gustafson, F. B.:
Russell S. : Hovering and Low- Charts for Estimation of Longitudinal-
Speed Performance and Control Stability Derivatives for a Helicopter
Characteristics of an Aerodynamic- Rotor in Forward Flight. TN 2309,
Servocontrolled Helicopter Rotor March 1951.
System as Determined on the
Langley Helicopter Tower. TN Mager, Artur: Generalization of
2086, May 1950. Boundary-Layer Momentum-Integral
Equations to Three-Dimensional
Flows Including Those of Rotating
THEORY System. TN 2310, March 1951.

(1.6,1) Harrington, Robert D.: Full-Scale-
Tunnel Investigation of the Static-
Dingeldein, Richard C. and Schaefer, Thrust Performance of a Coaxial
Raymond F. : Full-Scale Investi- Helicopter Rotor. TN 2311, March
gation of the Aerodynamic Charac- 1951.
teristics of a Typical Single-
Rotor Helicopter in Forward Flight.
Rept. 905, 1948. EXPERIMENTAL STUDIES

Gessow, Alfred and Amer, Kenneth B.: (1.6.2)
An Introduction to the Physical
Aspects of Helicopter Stability. Amer, Kenneth B.: Theory of Helicopter
Rept. 993, 1950. Damping in Pitch or Roll and a
Comparison with Flight Measure-
Morduchow, Morris: A Theoretical ments. TN 2136, October 1950.
Analysis of Elastic Vibrations of
Fixed-Ended and Hinged Helicopter Taylor, Marion K.: A Balsa-Dust Tech-
Blades in Hovering and Vertical nique for Air-Flow Visualization
Flight. TN 1999, January 1950. and its Application to Flow through
Model Helicopter Rotors in Static
Gessow, Alfred: An Analysis of the Thrust. TN 2220, November 1950.
Autorotative Performance of a
Helicopter Powered by Rotor-Tip POWER DRIVEN
Jet Units. TN 2154, July 1950. (1.6.2.1)

Amer, Kenneth B.: Theory of Hieli- Dingeldein, Richard C. and Schaefer,
copter Damping in Pitch or Roll Raymond F. : Full-Scale Investiga-
and a Comparison with Flight tion of the Aerodynamic Character-
Measurements. TN 2136, October istics of a Typical Single-Rotor
1950. Helicopter in Forward Flight.
Rept. 905, 1948.
Morduchow, M. and Hinchey, F. G.:
Theoretical Analysis of Oscilla-
tions in Hovering of Helicopter
Blades with Inclined and Offset
Flapping and Lagging Hinge Axes.
TN 2226, December 1950.








AERODYNAMICS
ROTORS (1.6) 57

Power Driven Ex-erimental Studies (Cont.)

Carpenter, Paul J. and Paulnock,
Russell S.: Hovering and Low-
Speed Performance and Control
Characteristics of an Aerodynamic-
Servocontrolled Helicopter Rotor
System as Determined on the
Langley Helicopter Tower. TN
2086, May 1950.

Taylor, Marion K.: A Balsa-Dust Tech-
nique for Air-Flow Visualization
and its Application to Flow through
Model Helicopter Rotors in Static
Thrust. TN 2220, November 1950.

Carpenter, Paul J.: Effects of Com-
pressibility on the Performance
of Two Full-Scale Helicopter
Rotors. TN 2277, January 1951.

Harrington, Robert D.: Full-Scale-
Tunnel Investigation of the Static-
Thrust Performance of a Coaxial
Helicopter Rotor. TN 2318, March
1951.

AUTOROTATING
(1.6.2.2)

Gessow, Alfred: An Analysis of the
Autorotative Performance of a
Helicopter Powered by Rotor-Tip
Jet Units. TN 2154, July 1950.







58 AERODYNAMICS




Aircraft


(1.7)


AIRPLANES Lomax, Harvard and Heaslet, Max. A.:
Damping-in-Roll Calculations for
(. 7.1) Slender Swept-Back Wings and
Slender Wing-Body Combinations.
Neihouse, Anshal I. and Pepoon, TN 1950, September 1949.
Philip W.: Dynamic Similitude
between a Model and a Full-Scale Spreiter, John R.: The Aerodynamic
Body for Model Investigation at Forces on Slender Plane- and
Full-Scale Mach Number. TN Cruciform-Wing and Body Combi-
2062, March 1950. nations. Rept. 962, 1950.

COMPONENTS IN COMBINATION Wick, Bradford H. and Graham, David:
(1.7.1.1) Exploratory Investigation of the Ef-
fect of Skewed Plain Nose Flaps on
Sivells, James C. and Spooner, the Low-Speed Characteristics of a
Stanley H. : Investigation in the Large-Scale Triangular-Wing-
Langley 19-Foot Pressure Tunnel Fuselage Model. RM A9K22,
of Two Wings of NACA 65-210 and January 1950.
64-210 Airfoil Sections with Vari-
ous Type Flaps. Rept. 942, 1949. Lubarsky, Bernard: Performance and
Load-Range Characteristics of
Kohler, M. and Mautz, W.: Pressure- Turbojet Engine in Transonic
Distribution Measurements on the Speed Range. TN 2088, May 1950.
Tail Surfaces of a Rotating Model
of the Design BFW M 31. TM Tucker, Warren A. and Piland,
1220, December 1949. Robert 0.: Estimation of the
Damping in Roll of Supersonic-
Shanks, Robert E.: Model Flight In- Leading-Edge Wing-Body Combi-
vestigation of a Nonlifting Winged nations. TN 2151, July 1950.
Tow Target. RM L50H30, Octo-
ber 1950. Roberts, John C. and Yaggy, Paul F.:
A Survey of the Flow at the Plane
Michael, William H., Jr.: Analysis of the Propeller of a Twin-Engine
of the Effects of Wing Interference Airplane. TN 2192, September
on the Tail Contributions to the 1950.
Rolling Derivatives. TN 2332,
April 1951. Rogallo, Vernon L.; Roberts, John C.;
and Oldaker, Merritt R.: Vibratory
Wing-Fuselage Stresses in Propellers Operating
(1.7.1. 1.1) in the Flow Field of a Wing-Nacelle-
Fuselage Combination. TN 2308,
Van Dyke, Milton D.: Aerodynamic March 1951.
Characteristics Including Scale
Effects of Several Wings and Wing-Nacelle
Bodies alone and in Combination (1. 7. 1. 2)
at a Mach Number of 1. 53. RM
A6K22, December 1946. Hanson, Frederick H., Jr. and
Dannenberg, Robert E.: Effect of
a Nacelle on the Low-Speed Aero-
dynamic Characteristics of a
Swept-Back Wing. RM A8E12,
July 1948.








AERODYNAMICS
AIRCRAFT (1.7) 59

'.ing-Nacelle Airolanes (Cont.) Letko, William and Riley, Donald R.:
Effect of an Unswept Wing on the
Lubarsky, Bernard: Performance and Contribution of Unswept-Tail Con-
Load-Range Characteristics of figurations to the Low-Speed Static-
Turbojet Engine in Transonic and Rolling-Stability Derivatives of
Speed Range. TN 2088, May 1950. a Midwing Airplane Model. TN
2175, August 1950.
Roberts, John C. and Yaggy, Paul F.:
A Survey of the Flow at the Plane Stone, Ralph W., Jr.; Burke, Sanger M.,
of the Propeller of a Twin-Engine Jr.; and Bihrle, William, Jr.: The
Airplane. TN 2192, September Aerodynamic Forces and Moments on
1950. a 1/10-Scale Model of a Fighter Air-
plane in Spinning Altitudes as Mea-
Rogallo, Vernon L.; Roberts, John C.; sured on a Rotary Balance in the
and Oldaker, Merritt R.: Vibra- Langley 20-Foot Free-Spinning Tun-
tory Stresses in Propellers Operat- nel. TN 2181, September 1950.
ing in the Flow Field of a Wing-
Nacelle-Fuselage Combinations. Klinar, Walter J. and Wilson, Jack H.:
TN 2308, March 1951. Spin-Tunnel Investigation of the Ef-
fects of Mass and Dimensional
Tail-Wing and Fuselage Variations on the Spinning Charac-
(1. 7.1.1. 3) teristics of a Low-Wing Single-
Vertical-Tail Model Typical of
Phillips, William H.: Appreciation and Personal-Owner Airplanes. TN
Prediction of Flying Qualities. 2352, May 1951.
Rept. 927, 1949.
Letko, William: Effect of Vertical-Tail
Well, Joseph and Sleeman, Area and Length on the Yawing
William G., Jr. : Prediction of the Stability Characteristics of a Model
Effects of Propeller Operation on having a 450 Sweptback Wing. TN
the Static Longitudinal Stability of 2358, May 1951.
Single-Engine Tractor Monoplanes
with Flaps Retracted. Rept. 941, External Stores
1949. (1.7.1.1.5)

Brewer, Jack D. and Lichtenstein Berman, Theodore: Spin-Tunnel Investi-
Jacob H.: Effect of Horizontal Tail gation of the Jettisoning of External
on Low-Speed Static Lateral Stabil- Fuel Tanks in Spins. RM L9J25,
ity Characteristics of a Model Hav- November 1949.
ing 450 Sweptback Wing and Tail
Surfaces. TN 2010, January 1950. SPECIFIC AIRPLANES
(1.7.1.2)
Huffschmid, A.: Investigation of the
Model ME 210 in the Spin Wind Nissen, James M.; Gadeberg, Burnett L.;
Tunnel of the DVL Fourth Partial and Hamilton, William T.: Correla-
Report Model with a Vee Tail. tion of the Drag Characteristics of a
TM 1222, April 1950. P-51B Airplane Obtained from High-
Speed Wind Tunnel and Flight Tests.
Queijo, M. J. and Wolhart, Walter D.: Rept. 916, 1948.
Experimental Investigation of the
Effect of Vertical-Tail Size and Steiner, Roy: An Analysis of Airspeeds
Length and of Fuselage Shape and Attained by a Douglas DC-4 Air-
Length on the Static Lateral Stabil- plane in Commerical Operations
ity Characteristics of a Model with during the Early Months of 1947.
450 Sweptback Wing and Tail Sur- RM L8K24, October 1949.
faces. TN 2168, August 1950.







AERODYNAMICS
60 AIRCRAFT (1.7)

Specific Airplanes (Cont.) PERFORMANCE
(1.7.1.3)
Faber, Stanley: Comparison of Effective-
ness of Coordinated Turns and Level Lovell, J. Calvin and Lipson, Stanley:
Sideslips for Correcting Lateral An Analysis of the Effect of Lift-
Displacement during Landing Ap- Drag Ratio and Stalling Speed on
proaches. RM L9129, December Landing-Flare Characteristics.
1949. TN 1930, September 1949.

Bird, John D. and Jaquet, Byron M.: Stephenson, Jack D.: The Effects of
A Study of the Use of Experimental Aerodynamic Brakes upon the Speed
Stability Derivatives in the Calcula- Characteristics of Airplanes. TN
tion of the Lateral Disturbed Mo- 1939, September 1949.
tions of a Swept-Wing Airplane and
Comparison with Flight Results. Stuper: Flight Experiences and Tests
TN 2013, January 1950. on Two Airplanes with Suction Slots.
TM 1232, January 1950.
Iluffschmid, i. : Investigation of the
Model ME 210 in the Spin Wind Tun- Horton, Elmer A.; Loftin, Laurence K., Jr.;
nel of the DVL Fourth Partial and Racisz, Stanley F.: Analysis of
Report Model with a Vee Tail. the Effects of Boundary-Layer Control
TM 1222, April 1950. on the Power-Off Landing Performance
Characteristics of a Liaison Type of
Coleman, Thomas L.: An Analysis of Airplane. TN 2143, August 1950.
the Normal Accelerations and Air-
speeds of Several Lockheed Con-
stellation L-649 Airplanes in Post- MISSILES
war Commercial Transport Opera-
tions over the Eastern Part of the (1.7. 2)
United States. RM L9E18a, April
1950. Chapman, Dean R. and Perkins,
Edward W.: Experimental Investiga-
Fisher, Lloyd J. and Hoffman, Edward L.: tion of the Effects of Viscosity on the
Model Ditching Investigation of the Drag of Bodies of Revolution at a
Douglas DC-4 and DC-6 Airplanes. Mach Number of 1. 5. RM A7A31a,
RM L9K02a, May 1950. April 1947.

Talmage, Donald B.; Reeder, John P.; Neihouse, Anslal I. and Pepoon,
and Matthews, Ruth G.: Flight Philip W.: Dynamic Similitude
Investigation of Longitudinal Stabil- between a Model and a Full-Scale
ity and Control Characteristics and Body for Model Investigation at
Stalling Characteristics of a C-45D Full-Scale Mach Number. TN
Airplane. RM L9L21, May 1950. 2062, March 1950.

Mathews, Charles W.; Talmage, Soule, Harold V. and Sabol,
Donald B.; and Whitten, James B.: Alexander P.: Development and
Effects of Longitudinal Stability and Preliminary Investigation of a
Control Characteristics of a B-29 Method of Obtaining Hypersonic
Airplane of Variations in Stick- Aerodynamic Data by Firing
Force and Control-Rate Character- Models through Highly Cooled
istics Obtained through Use of a Gases. TN 2120, July 1950.
Booster in the Elevator-Control
System. TN 2238, February 1951. Adams, Gaynor J.: Theoretical Damping
in Roll and Rolling Effectiveness
of Slender Cruciform Wings. TN
2270, January 1951.








AERODYNAMICS
AIRCRAFT (1.7) 61

Hissiles (Cont.)

Henry, John R. and Bennett, J. Buel:
Method for Calculation of Ram-Jet ROTATING WING AIRCRAFT
Performance. TN 2357, June 1951.
(1.7.3)
COMPONENTS IN COMBINATION
(1.7.2.1) AUTOGIROS
(1.7.3.1)
Spreiter, John R. : The Aerodynamic
Forces on Slender Plane- and Gessow, Alfred and Amer, Kenneth B.:
Cruciform-Wing and Body Combina- An Introduction to the Physical As-
tions. Rept. 962, 1950. pects of Helicopter Stability.
Rept. 993, 1950.
Wing-Body
(1. 7. 2. 1. 1) Amer, Kenneth B. and Gustafson, F. B.:
Charts for Estimation of Longitudinal-
Van Dyke, Milton D.: Aerodynamic Stability Derivatives for a Helicopter
Characteristics Including Scale Ef- Rotor in Forward Flight. TN 2309.
fects of Several Wings and Bodies March 1951.
alone and in Combination at Mach
Number of 1. 53. RM A6K22, HELICOPTERS
December 1946. (1.7.3.2)

Tucker, Warren A. and Piland, Dingeldein, Richard C. and Schaefer,
Robert 0. : Estimation of the Damp- Raymond F. : Full-Scale Investiga-
ing in Roll of Supersonic-Leading- tion of the Aerodynamic Character-
Edge Wing-Body Combinations. istics of a Typical Single-Rotor
TN 2151, July 1950. Helicopter in Forward Flight.
Rept. 905, 1948.
T ail-Body
(1.7.2. 1. 2) Gustafson, F. B.; Amer, Kenneth B.;
Haig, C. R ; and Reeder, J. P.:
Spahr, J. Richard and Dickey, Robert R.: Longitudinal Flying Qualities of
Effect of Tail Surfaces on the Base Several Single-Rotor Helicopters
Drag of a Body of Revolution at in Forward Flight. TN 1983,
Mach Numbers of 1. 5 and 2.0. TN November 1949.
2360, April 1951.
Schaefer, Raymond F. and Smith,
Jet Interference Hamilton A.: Aerodynamic Charac-
(1.7.2.1.3) teristics of the NACA 8-H-12 Air-
foil Section at Six Reynolds Num-
Szablewski, W.: The Diffusion of a Hot bers from 1.8 x 106 to 11.0 x 106.
Air Jet in Air in Motion. TM TN 1998, December 1949.
1288, December 1950.
Gessow, Alfred and Amer, Kenneth B.:
SPECIFIC MISSILES An Introduction to the Physical As-
(1.7.2.2) pects of Helicopter Stability.
Rept. 993, 1950.
Sponder, E. W.: Investigation of Lateral
Stability of a Glide Bomb Using Morduchow, Morris: A Theoretical
Automatic Control having no Time Analysis of Elastic Vibrations of
Lag. TM 1248, August 1950. Fixed-Ended and Hinged Helicopter
Blades in Hovering and Vertical
Flight. TN 1999, January 1950.







AERODYNAMICS
62 AIRCRAFT (1.7)

Helicopters Rotating Wing Aircraft (Cont.)

Smith, Hamilton A. and Schaefer,
Raymond F.: Aerodynamic Charac-
teristics at Reynolds Numbers of
3.0 x 106 and 6.0 x 106 of Three
Airfoil Sections Formed by Cutting
off Various Amounts from the Rear
Portion of the NACA 0012 Airfoil
Section. TN 2074, April 1950.

Carpenter, Paul J. and Paulnock,
Russell S.: Hovering and Low-
Speed Performance and Control
Characteristics of an Aerodynamic-
Servocontrolled Helicopter Rotor
System as Determined on the
Langley Helicopter Tower. TN
2086, May 1950.

Amer, Kenneth B. : Theory of Heli-
copter Damping in Pitch or Roll
and a Comparison with Flight
Measurements. TN 2136, October
1950.

Gessow, Alfred: An Analysis of the
Autorotative Performance of a
Helicopter Powered by Rotor-Tip
Jet Units. TN 2154, July 1950.

Morduchow, M. and Hinchey, F G.:
Theoretical Analysis of Oscilla-
tions in Hovering of Helicopter
Blades with Inclined and Offset
Flapping and Lagging Hinge Axes.
TN 2226, December 1950.

Carpenter, Paul J.: Effects of Com-
pressibility on the Performance of
Two Full-Scale Helicopter Rotors.
TN 2277, January 1951.

Amer. Kenneth B. and Gustafson, F. B.:
Charts for Estimation of Longi-
tudinal-Stability Derivatives for a
Helicopter Rotor in Forward Flight.
TN 2309, March 1951.

Harrington, Robert D.: Full-Scale-
Tunnel Investigation of the Static-
Thrust Performance of a Coaxial
Helicopter Rotor. TN 2318,
March 1951.

de Guillenchmidt, P.: Calculation of the
Bending Stresses in Helicopter
Rotor Blades. TM 1312, March 1951.








AERODYNAMICS 63





Stability and Control


(1.8)


Kohler, M. and Mautz, W.: Pressure- Hanson, Frederick H., Jr. and
Distribution Measurements on the Dannenberg, Robert E. : Effect of
Tail Surfaces of a Rotating Model a Nacelle on the Low-Speed Aero-
of the Design BFW M 31. TM dynamic Characteristics of a
1220, December 1949. Swept-Back Wing. RM A8E12,
July 1948.
Gessow, Alfred and Amer, Kenneth B.:
An Introduction to the Physical Harmon, Sidney M.: Stability Deriva-
Aspects of Helicopter Stability. tives of Thin Rectangular Wings at
Rept. 993, '1950. Supersonic Speeds. Wing Diagonals
ahead of Tip Mach Lines. Rept. 925,
Carpenter, Paul J. and Paulnock, 1949.
Russell S.: Hovering and Low-
Speed Performance and Control Phillips, William H.: Appreciation
Characteristics of an Aerodynamic- and Prediction of Flying Qualities.
Servocontrolled Helicopter Rotor Rept. 927, 1949.
System as Determined on the
Langley Helicopter Tower. TN Weil, Joseph and Sleeman,
2086, May 1950. William G., Jr.: Prediction of the
Effects of Propeller Operation on
Amer, Kenneth B.: Theory of Heli- the Static Longitudinal Stability of
copter Damping in Pitch or Roll Single-Engine Tractor Monoplanes
and a Comparison with Flight with Flaps Retracted. Rept. 941,
Measurements. TN 2136, Octo- 1949.
ber 1950.
Harmon, Sidney M.: Theoretical
Longitudinal Static Stability Relations between the Stability
(1.8.1.1.1) Derivatives of a Wing in Direct
and in Reverse Supersonic Flow.
Wilson, Herbert A., Jr. and Lovell, TN 1943, September 1949.
J. Calvin: Full-Scale Investigation
of the Maximum Lift and Flow Char- Piland, Robert 0.: Summary of the
acteristics of an Airplane Having Theoretical Lift, Damping-in-Roll,
Approximately Triangular Plan and Center-of-Pressure Charac-
Form. RM L6K20, February 1947. teristics of Various Wing Plan
Forms at Supersonic Speeds. TN
Purser, Paul E. and Spearman, 1977, October 1949.
M. Leroy: Wind-Tunnel Tests at
Low Speed of Swept and Yawed Wings Gustafson, F. B.; Amer, Kenneth B.;
having Various Plan Forms. RM Haig, C. R.; and Reeder, J. P.:
L7D23, May 1947. Longitudinal Flying Qualities of
Several Single-Rotor Helicopters
DeYoung, John and Harper, Charles W.: in Forward Flight. TN 1983,
Theoretical Symmetric Span Loading November 1949.
at Subsonic Speeds for Wings having
Arbitrary Plan Form. Rept. 921,
1948.







AERODYNAMICS
64 STABILITY AND CONTROL (1.8)

Longitudinal Static Stability (Cont.) Talmage, Donald B.; Reeder, John P.;
and Matthews, Ruth G. : Flight In-
Heaslet, Max. A. and Lomax, Harvard: vestigation of Longitudinal Stability
The Calculation of Downwash behind and Control Characteristics and
Supersonic Wings with an Application Stalling Characteristics of a C-54D
to Triangular Plan Forms. Rept. Airplane. RM L9L21, May 1950.
957, 1950.
Haefeli, Rudolph C.; Mirels, Harold;
Mirels, Harold and Haefeli, Rudolph C.: and Cummings, John L.: Charts
Line-Vortex Theory for Calcula- for Estimating Downwash behind
tion of Supersonic Downwash. Rept. Rectangular, Trapezoidal, and
983, 1950. Triangular Wings at Supersonic
Speeds. TN 2141, August 1950.
Brewer, Jack D. and Lichtenstein,
Jacob I. : Effect of Horizontal Johnson, Harold S. and Hagerman,
Tail on Low-Speed Static Lateral John R.: Wind-Tunnel Investigation
Stability Characteristics of a at Low Speed of a 450 Sweptback Un-
Model having 450 Sweptback Wing tapered Semispan Wing of Aspect
and Tail Surfaces. TN 2010, Ratio 1. 59 Equipped with Various
January 1950. 25-Percent-Chord Plain Flaps.
TN 2169, August 1950.
Lange, Roy H. and McLemore, Huel C.:
Static Longitudinal Stability and Letko, William and Riley, Donald R.:
Control of a Convertible-Type Air- Effect of an Unswept Wing on the
plane as Affected by Articulated- Contribution of Unswept-Tail Con-
and Rigid-Propeller Operation. figurations to the Low-Speed Static-
TN 2014, February 1950. and Rolling-Stability Derivatives of
a Midwing Airplane Model. TN
Ribner, Herbert S.: Time-Dependent 2175, August 1950.
Downwash at the Tail and the
Pitching Moment Due to Normal Riebe, John M. and Watson, James M.:
Acceleration at Supersonic Speeds. The Effect of End Plates on Swept
TN 2042, February 1950. Wings at Low Speed. TN 2229,
November 1950.
Schade, Robert 0.: Free-Flight-Tunnel
Investigation of Dynamic Longi- Mathews, Charles W.; Talmage,
tudinal Stability as Influenced by Donald B.; and Whitten, James B.:
the Static Stability Measured in Effects on Longitudinal Stability and
Wind-Tunnel Force Tests under Control Characteristics of a B-29
Conditions of Constant Thrust and Airplane of Variations in Stick-Force
Constant Power. TN 2075, April and Control-Rate Characteristics
1950. Obtained through Use of a Booster
in the Elevator-Control System.
Johnson, Harold S. and Hagerman, TN 2238, February 1951.
John R.: Wind-Tunnel Investigation
at Low Speed of an Unswept Un- Amer, Kenneth B. and Gustafson, F. B.:
tapered Semispan Wing of Aspect Charts for Estimation of Longitudinal-
Ratio 3.13 Equipped with Various Stability Derivatives for a Helicopter
25-Percent-Chord Plain Flaps. Rotor in Forward Flight. TN 2309,
TN 2080, April 1950. March 1951.

Scher, Stanley H. and Draper, John W.: Naeseth, Rodger L. and O'Hare,
The Effects of Stability of Spin- William M.: Effect of Aspect Ratio
Recovery Tail Parachutes on the on the Low-Speed Lateral Control
Behavior of Airplanes in Gliding Characteristics of Unswept Un-
Flight and in Spins. TN 2098, tapered Low-Aspect-Ratio Wings.
May 1950. TN 2348, May 1951.








AERODYNAMICS
STABILITY AND CONTROL (1.8) 65

Lateral Static Stability Queijo, M. J. and Wolhart, Walter D.:
(1.8.1. 1.2) Experimental Investigation of the
Effect of Vertical-Tail Size and
Purser, Paul E. and Spearman, Length and of Fuselage Shape and
M. Leroy: Wind-Tunnel Tests at Length on the Static Lateral
Low Speed of Swept and Yawed Stability Characteristics of a
Wings having Various Plan Forms. Model with 450 Sweptback Wing
RM L7D23, May 1947. and Tail Surfaces. TN 2168,
August 1950.
Harmon, Sidney M.: Stability Deriva-
tives of Thin Rectangular Wings at Letko, William and Riley, Donald R :
Supersonic Speeds. Wing Diagonals Effect of an Unswept Wing on the
ahead of Tip Mach Lines. Rept. Contribution of Unswept-Tail Con-
925, 1949. figurations to the Low-Speed
Static- and Rolling-Stability Deri-
Phillips, William H.: Appreciation and vatives of a Midwing Airplane
Prediction of Flying Qualities. Model. TN 2175, August 1950.
Rept. 927, 1949.
Riebe, John M. and Watson, James M.:
Kauffman, William M.; Liddell, The Effect of End Plates on Swept
Charles J., Jr.; Smith, Allan; Wings at Low Speed. TN 2229,
and Van Dyke, Rudolph D., Jr.: November 1950.
An Apparatus for Varying Effective
Dihedral in Flight with Application Lovell, Powell M., Jr.: A Compari-
to a Study of Tolerable Dihedral on son of the Lateral Controllability
a Conventional Fighter Airplane. with Flap and Plug Ailerons on a
Rept. 948, 1949. Sweptback-Wing Model Having
Full-Span Flaps. TN 2247, De-
Brewer, Jack D. and Lichtenstein, cember 1950.
Jacob I.: Effect of Horizontal Tail
on Low-Speed Static Lateral Stabil- Lampert, Seymour: Rolling and Yaw-
ity Characteristics of a Model hav- ing Moments for Swept-Back
ing 450 Sweptback Wing and Tail Wings in Sideslip at Supersonic
Surfaces. TN 2010, January 1950. Speeds. TN 2262, January 1951.

Bird, John D. anu Jaquet, Byron M.: Naeseth, Rodger L. and O'Hare,
a- Study of the Use of Experimental William M.: Effect of Aspect
Stability Derivatives in the Calcula- Ratio on the Low-Speed Lateral
tion of the Lateral Disturbed Mo- Control Characteristics of Un-
tions of a Swept-Wing Airplane and swept Untapered Low-Aspect-
Comparison with Flight Results. Ratio Wings. TN 2348, May 1951.
TN 2013, January 1950.
Directional Static Stability
Lovell, Powell M., Jr. and Stassi, Paul P.: (1.8. 1. 1.3)
A Comparison of the Lateral Con-
trollability with Flap and Plug Ailer- Harmon, Sidney M.: Stability Deriva-
ons on a Sweptback-Wing Model. tives of Thin Rectangular Wings
TN 2089, May 1950. at Supersonic Speeds. Wing
Diagonals ahead of Tip Mach Lines.
Margolis, Kenneth: Theoretical Calcula- Rept. 925, 1949.
tions of the Lateral Force and Yaw-
ing Moment Due to Rolling at Super-
sonic Speeds for Sweptback Tapered
Wings with Streamwise Tips. Sub-
sonic Leading Edges. TN 2122,
June 1950.







AERODYNAMICS
66 STABILITY AND CONTROL (1.8)

Dir ectiontal Static Stability (Cont.) Curfman, Howard J., Jr. and Gardiner,
Robert A.: Method for Determining
Phillips, William IH.: Appreciation and the Frequency-Response Character-
Prediction of Flying Qualities. istics of an Element or System from
Rept. 927, 1949. the System Transient Output Response
to a Known Input Function. Rept.
Johnson, Harold I.: Flight Investigation 984, 1950.
of the Effect of Various Vertical-
Tail Modifications on the Directional Gardiner, Robert A.; Zarovsky, Jacob;
Stability and Control Characteristics and Ankenbruck, H. O.: An Investi-
of a Propeller-Driven Fighter Air- gation of the Stability of a System
plane. Rept. 973, 1950. Composed of a Subsonic Canard Air-
frame and a Canted-Axis Gyroscope
Brewer, Jack D. and Lichtenstein, Automatic Pilot. TN 2004, January
Jacob H. : Effect of Horizontal 1950.
Tail on Low-Speed Static Lateral
Stability Characteristics of a Model Bird, John D and Jaquet, Byron M. : A
having 450 Sweptback Wing and Tail Study of the Use of Experimental
Surfaces. TN 2010, January 1950. Stability Derivatives in the Calcula-
tion of the Lateral Disturbed Motions
Bird, John D. and Jaquet, Byron M.: of a Swept-Wing Airplane and Com-
A Study of the Use of Experimental parison with Flight Results. TN
Stability Derivatives in the Calcu- 2013, 1950.
lation of the Lateral Disturbed Mo-
tions of a Swept-Wing Airplane and Niehouse, Anshal I. and Pepoon,
Comparison with Flight Results. Philip W.: Dynamic Similitude be-
TN 2013, January 1950. tween a Model and a Full-Scale Body
for Model Investigation at Full-Scale
Scher, Stanley H. and Draper, John W.: Mach Number. TN 2062, March 1950.
The Effects of Stability of Spin-
Recovery Tail Parachutes on the Sponder, E. W.: Investigation of Lateral
Behavior of Airplanes in Gliding Stability of a Glide Bomb Using
Flight and in Spins. TN 2098, Automatic Control having no Time
May 1950. Lag. TM 1248, August 1950.

Letko, William and Riley, Donald R.: Turner, Howard L.: Measurement of the
Effect of an Unswept Wing on the Moments of Inertia of an Airplane by
Contribution of Unswept-Tail Con- a Simplified Method. TN 2201,
figurations to the Low-Speed Static- October 1950.
and Rolling-Stability Derivatives
of a Midwing Airplane Model. TN Lomax, Harvard; Heaslet, Max. A.; and
2175, August 1950. Fuller, Franklyn B.: Three-
Dimensional, Unsteady-Lift Prob-
Queijo, M. J. and Wolhart, Walter D.: lems in High-Speed Flight Basic
Experimental Investigation of the Concepts. TN 2256, December 1950.
Effect of Vertical-Tail Size and
Length and of Fuselage Shape and Schy, Albert A. : A Theoretical Analysis
Length on the Static Lateral Stabil- of the Effects of Fuel Motion on Air-
ity Characteristics of a Model with plane Dynamics. TN 2280, January
450 Sweptback Wing and Tail Sur- 1951.
faces. TN 2168, August 1950.
Longitudinal Dynamic Stability
DYNAMIC STABILITY (1.8.1.2.1)
(1.8.1.2)
Greenberg, Harry: Frequency-Response
Evvard, John C.: Use of Source Distri- Method for Determination of Dynamic
butions for Evaluating Theoretical Stability Characteristics of Airplanes
Aerodynamics of Thin Finite Wings with Automatic Controls. Rept. 882,
at Supersonic Speeds. Rept. 951, 1947.
1950.








AERODYNAMICS
STABILITY AND CONTROL (1.8) 67

Longitudinal Dmnamic Stability (Cont.) Matheny, Cloyce E.: Maximum Pitch-
ing Angular Accelerations of Air-
Phillips, William H.: Appreciation planes Measured in Flight. TN
and Prediction of Flying Qualities. 2103, May 1950.
Rept. 927, 1949.
Mathews, Charles W.; Talmage,
Filzek, B.: Investigations on the Stability, Donald B.; and Whitten, James B.:
Oscillation, and Stress Conditions Effects on Longitudinal Stability
of Airplanes with Tab Control. and Control Characteristics of a
First Partial Report Derivation B-29 Airplanes of Variations in
of the Equations of Motion and Stick-Force and Control-Rate
their General Solutions. TM 1197, Characteristics Obtained through
September 1949. Use of a Booster in the Elevator-
Control System. TN 2238, Febru-
Filzek, B.: Investigations on the Stabil- ary 1951.
ity, Oscillation, and Stress Condi-
tions of Airplanes with Tab Control. Amer, Kenneth B. and Gustafson, F. B.:
Second Partial Report Application Charts for Estimation of
of the Solutions Obtained in the Longitudinal-Stability Derivatives
First Partial Report to Tab- for a Helicopter Rotor in Forward
Controlled Airplanes. TM 1198, Flight. TN 2309, March 1951.
September 1949.
Greenberg, Harry: A Survey of Meth-
Gustafson, F. B.; Amer, Kenneth B.; ods for Determining Stability
Haig, C. R.; and Reeder, J. P.: Parameters of an Airplane from
Longitudinal Flying Qualities of Dynamic Flight Measurements.
Several Single-Rotor Helicopters TN 2340, April 1951.
in Forward Flight. TN 1983,
November 1949. Shinbrot, Marvin: A Least-Squares
Curve-Fitting Method with Ap-
Mokrzycki, G. A.: Application of the plications to the Calculation of
Laplace Transformation to the Stability Coefficients from
Solution of the Lateral and Longi- Transient-Response Data. TN
tudinal Stability Equations. TN 2341, April 1951.
2002, January 1950.
Donegan, James J. and Pearson,
Mazelsky, Bernard and Diederich, Henry A.: Matrix Method of
Franklin W.: A Method of Deter- Determining the Longitudinal-
mining the Effect of Airplane Stability Coefficients and Fre-
Stability on the Gust Load Factor. quency Response of an Aircraft
TN 2035, February 1950. from Transient Flight Data. TN
2371, June 1951.
Schade, Robert 0.: Free-Flight-Tunnel
Investigation of Dynamic Longitudi- Lateral and Directional Dynamic Stability
nal Stability as Influenced by the (1.8.1.2.2)
Static Stability Measured in Wind-
Tunnel Force Tests under Condi- Greenberg, Harry: Frequency-Response
tions of Constant Thrust and Method for Determination of Dynam-
Constant Power. TN 2075, April ic Stability Characteristics of Air-
1950. planes with Automatic Controls.
Rept. 882, 1947.
Scher, Stanley H. and Draper, John W.:
The Effects of Stability of Spin-
Recovery Tail Parachutes on the
Behavior of Airplanes in Gliding
Flight and in Spins. TN 2098,
May 1950.







AERODYNAMICS
68 STABILITY AND CONTROL (1. 8)

Lateral and Directional Dynamic Stability Beckhardt, Arnold R.: A Theoretical
(Cont.) Investigation of the Effect on the
Phillips, William H.: Appreciation Lateral Oscillations of an Airplane
and Prediction of Flying Qualities. of an Automatic Control Sensitive
Rept. 927, 1949. to Yawing Accelerations. TN 2006,
January 1950.
Sternfield, Leonard and Gates,
Ordway B., Jr.: A Simplified Scher, Stanley H. and Draper, John W.:
Method for the Determination and The Effects of Stability of Spin-
Analysis of the Neutral-Lateral- Recovery Tail Parachutes on the
Oscillatory-Stability Boundary. Behavior of Airplanes in Gliding
Rept. 943, 1949. Flight and in Spins. TN 2098,
May 1950.
Kauffman, William M.; Liddell,
Charles J., Jr.; Smith, Allan; Murray, Harry E. and Grant,
and Van Dyke, Rudolph D., Jr.: Frederick C.: Method of Calculat-
An Apparatus for Varying Effec- ing the Lateral Motions of Aircraft
tive Dihedral in Flight with Ap- Based on the Laplace Transform.
plication to a Study of Tolerable TN 2129, July 1950.
Dihedral on a Conventional
Fighter Airplane. Rept. 948, Letko, William and Riley, Donald R.:
1949. Effect of an Unswept Wing on the
Contribution of Unswept-Tail Con-
Campbell, John P. and Goodman, figurations to the Low-Speed Static-
Alex: A Semiempirical Method and Rolling-Stability Derivatives
for Estimating the Rolling Moment of a Midwing Airplane Model. TN
Due to Yawing of Airplanes. TN 2175, August 1950.
1984, December 1949.
Stough, Carl J. and Kauffman, William M.:
McKinney, Marion O., Jr.: Analysis A Flight Investigation and Analysis of
of Means of Improving the Un- the Lateral-Oscillation Characteris-
controlled Lateral Motions of tics of an Airplane. TN 2195, Octo-
Personal Airplanes. TN 1997, ber 1950.
December 1949.
Shanks, Robert E.: Model Flight Inves-
Johnson, Harold I.: Flight Investiga- tigation of a Nonlifting Winged Tow
tion of the Effect of Various Target. RM L50H30, October 1950.
Vertical-Tail Modifications on
the Directional Stability and Control Sternfield, Leonard: Some Effects of
Characteristics of a Propeller- Nonlinear Variation in the Directional-
Driven Fighter Airplane. Rept. Stability and Damping-in-Yawing
973, 1950. Derivatives on the Lateral Stability
of an Airplane. TN 2233, November
Mokrzycki, G. A.: Application of the 1950.
Laplace Transformation to the
Solution of the Lateral and Longi- Gates, Ordway B., Jr. and Schy, Albert A.:
tudinal Stability Equations. TN A Theoretical Method of Determining
2002, January 1950. the Control Gearing and Time Lag
Necessary for a Specified Damping
Sternfield, Leonard and Gates, of an Aircraft Equipped with a
Ordway B., Jr.: A Theoretical Constant-Time-Lag Autopilot. TN
Analysis of the Effect of Time 2307, March 1951.
Lag in an Automatic Stabilization
System on the Lateral Oscillatory Hewes, Donald E.: The Effects of Mass
Stability of an Airplane. TN 2005, Distribution on the Low-Speed Dy-
January 1950. namic Lateral Stability and Control
Characteristics of a Model with a
450 Sweptback Wing. TN 2313,
March 1951.









AERODYNAMICS
STABILITY AND CONTROL (1.8) 69

Lateral nd Directional Dynamic Stability Campbell, John P. and Goodman, Alex:
(Gont. A Semiempirical Method for Esti-
Michael, William H., Jr.: Analysis of mating the Rolling Moment Due to
the Effects of Wing Interference on Yawing of Airplanes. TN 1984,
the Tail Contributions to the Rolling December 1949.
Derivatives. TN 2332, April 1951.
Goodman, Alex and Fisher, Lewis R.:
Letko, William: Effect of Vertical-Tail Investigation at Low Speeds of the
Area and Length on the Yawing Effect of Aspect Ratio and Sweep
Stability Characteristics of a Model on Rolling Stability Derivatives of
having a 450 Sweptback Wing. TN Untapered Wings. Rept. 968, 1950.
2358, May 1951.
Bird, John D.: Some Theoretical Low-
Damping Derivatives Speed Span Loading Characteristics
(1. 8. 1.2.3) of Swept Wings in Roll and Sideslip.
Rept. 969, 1950.
Brown, Clinton E. and Adams, Mac C.:
Damping in Pitch and Roll of Tri- Malvestuto, Frank S., Jr.; Margolis,
angular Wings at Supersonic Kenneth; and Ribner, Herbert S.:
Speeds. Rept. 892, 1948. Theoretical Lift and Damping in
Roll at Supersonic Speeds of Thin
Heaslet, Max. A. and Lomax, Harvard: Sweptback Tapered Wings with
The Use of Source-Sink and Doublet Streamwise Tips, Subsonic Lead-
Distributions Extended to the Solu- ing Edges and Supersonic Trailing
tion of Arbitrary Boundary Value Edges. Rept. 970, 1950.
Problems in Supersonic Flow.
Rept. 900, 1948. Malvestuto, Frank S., Jr. and Margolis,
Kenneth: Theoretical Stability Deriva-
Ribner, Herbert S. and Malvestuto, tives of Thin Sweptback Wings Tapered
Frank S., Jr.: Stability Deriva- to a Point with Sweptback or Swept-
tives of Triangular Wings at Su- forward Trailing Edges for A Limited
personic Speeds. Rept. 908, 1948. Range of Supersonic Speeds. Rept.
971, 1950.
Harmon, Sidney M.: Stability Derivatives
of Thin Rectangular Wings at Super- Tucker, Warren A. and Nelson, Robert L.:
sonic Speeds. Wing Diagonals ahead The Effect of Torsional Flexibility
of Tip Mach Lines. Rept. 925, 1949. on the Rolling Characteristics at
Supersonic Speeds of Tapered Un-
Harmon, Sidney M.: Theoretical Rela- swept Wings. Rept. 972, 1950.
tions between the Stability Deriva-
tives of a Wing in Direct and in Brown, Clinton E.: The Reversibility
Reverse Supersonic Flow. TN Theorem for Thin Airfoils in Sub-
1943, September 1949. sonic and Supersonic Flow. Rept.
986, 1950.
Lomax, Harvard and Heaslet, Max. A.:
Damping-in-Roll Calculations for Bird, John D. and Jaquet, Byron M.:
Slender Swept-Back Wings and A Study of the Use of Experimental
Slender Wing-Body Combinations. Stability Derivatives in the Calcula-
TN 1950, September 1949. tion of the Lateral Disturbed Mo-
tions of a Swept-Wing Airplane and
Piland, Robert 0.: Summary of the Comparison with Flight Results.
Theoretical Lift, Damping-in-Roll, TN 2013, January 1950.
and Center-of-Pressure Character-
istics of Various Wing Plan Forms Moskowitz, Barry and Moeckel, W. E.:
at Supersonic Speeds. TN 1977, First-Order Tiieory for Unsteady
October 1949. Motion of Thin Wings at Supersonic
Speeds. TN 2034, February 1950.






AERODYNAMICS
70 STABILITY AND CONTROL (1.8)

Damping Derivatives Stability (Cont.) Amer, Kenneth B.: Theory of Helicopter
Damping in Pitch or Roll and a
Walker, Harold J. and Ballantyne, Comparison with Flight Measure-
Mary B.: Pressure Distribution ments. TN 2136, October 1950.
and Damping in Steady Roll at
Supersonic Mach Numbers of Flat Walker, Harold J. and Ballantyne,
Swept-Back Wings witii Subsonic Mary B.: Pressure Distribution
Edges. TN 2047, March 1950. and Damping in Steady Pitch at
Supersonic Mach Numbers of Flat
Margolis, Kenneth: Theoretical Lift Swept-Back Wings having all Edges
and Damping in Roll of Thin Swept- Subsonic. TN 2197, October 1950.
back Tapered Wings with Raked-In
and Cross-Stream Wing Tips at Hassell, James L. and Bennett,
Supersonic Speeds. Subsonic Lead- Charles V.: The Dynamic Lateral
ing Edges. TN 2048, March 1950. Control Characteristics of Airplane
Models having Unswept Wings with
Harmon, Sidney M. and Jeffreys, Round- and Sharp-Leading-Edge
Isabella: Theoretical Lift and Sections. TN 2219, November 1950.
Damping in Roll of Thin Wings with
Arbitrary Sweep and Taper at Su- Sternfield, Leonard: Some Effects of
personic Speeds. Supersonic Lead- Nonlinear Variation in the
ing and Trailing Edges. TN 2114, Directional-Stability and Damping-
May 1950. in-Yawing Derivatives on the
Lateral Stability of an Airplane. TN
Tucker, Warren A. and Piland, Robert 0.: 2233, November 1950.
Estimation of the Damping in Roll of
Supersonic-Leading-Edge Wing-Body Adams, Gaynor J.: Theoretical Damping
Combinations. TN 2151, July 1950. in Roll and Rolling Effectiveness of
Slender Cruciform Wings. TN 2270,
Harmon, Sidney M. and Martin, John C.: January 1951.
Theoretical Calculations of the
Lateral Force and Yawing Moment Sivells, James C. and Westrick,
Due to Rolling at Supersonic Speeds Gertrude C.: Method for Calculating
for Sweptback Tapered Wings with Lift Distributions for Unswept Wings
Streamwise Tips. Supersonic with Flaps or Ailerons by Use of
Leading Edges. TN 2156, July 1950. Nonlinear Section Lift Data. TN
2283, January 1951.
Ribner, Herbert S.: On the Effect of
Subsonic Trailing Edges on Damping Ribner, Herbert S.: Damping in Roll of
in Roll and Pitch of Thin Sweptback Cruciform and Some Related Delta
Wings in a Supersonic Stream. TN Wings at Supersonic Speeds. TN
2146, August 1950. 2285, February 1951.

Ribner, Herbert S.: Some Conical and Malvestuto, Frank S., Jr. and Hoover,
Quasi-Conical Flows in Linearized Dorothy M.: Lift and Pitching
Supersonic-Wing Theory. TN 2147, Derivatives of Thin Sweptback
August 1950. Tapered Wings with Streamwise
Tips and Subsonic Leading Edges
Letko, William and Riley, Donald R.: at Supersonic Speeds. TN 2294,
Effect of an Unswept Wing on the February 1951.
Contribution of Unswept-Tail Con-
figurations to the Low-Speed Static- Malvestuto, Frank S., Jr. and Hoover,
and Rolling-Stability Derivatives of Dorothy M.: Supersonic Lift and
a Midwing Airplane Model. TN Pitching Moment of Thin Sweptback
2175, August 1950. Tapered Wings Produced by Constant
Vertical Acceleration. Subsonic
Leading Edges and Supersonic Trail-
ing Edges. TN 2315, March 1951.









AERODYNAMICS
STABILITY AND CONTROL (1.8) 71

Damping Derivatives Stability (Cont.) LONGITUDINAL CONTROL
(1.8. 2. 1)
Michael, William H., Jr.: Analysis of
the Effects of Wing Interference on Boddy, Lee E. and Williams, Walter C.:
the Tail Contributions to the Roll- Summary and Analysis of Data on
ing Derivatives. TN 2332, April Dive-Recovery Flaps. RM A7F09,
1951. June 1947.

Diederich, Franklin W.: A Plan-Form Phillips, William H.: Appreciation and
Parameter for Correlating Certain Prediction of Flying Qualities.
Aerodynamic Characteristics of Rept. 927, 1949.
Swept Wings. TN 2335, April 1951.
Tucker, Warren A. and Nelson, Robert L.:
Greenberg, Harry: A Survey of Methods Theoretical Characteristics in Super-
for Determining Stability Param- sonic Flow of Two Types of Control
eters of an Airplane from Dynamic Surfaces on Triangular Wings. Rept.
Flight Measurements. TN 2340, 939, 1949.
April 1951.
Well, Joseph and Sleeman, William G., Jr.:
Shinbrot, Marvin: A Least-Squares Prediction of the Effects of Propeller
Curve-Fitting Method with Applica- Operation on the Static Longitudinal
tions to the Calculation of Stability Stability of Single-Engine Tractor
Coefficients from Transient- Monoplanes with Flaps Retracted.
Response Data. TN 2341, April Rept. 941, 1949.
1951.
Filzek, B.: Investigation on the Stability,
Letko, William: Effect of Vertical- Oscillation, and Stress Conditions of
Tail Area and Length on the Yaw- Airplanes with Tab Control. First
ing Stability Characteristics of a Partial Report Derivation of the
Model having a 450 Sweptback Wing. Equations of Mution and their Gen-
TN 2358, May 1951. eral Solutions. TM 1197, September
1949.
Donegan, James J. and Pearson,
Henry A.: Matrix Method of De- Filzek, B. : Investigations on the Stabil-
termining the Longitudinal- ity, Oscillation, and Stress Condi-
Stability Coefficients and Fre- tions of Airplanes with Tab Control.
quency Response of an Aircraft Second Partial Report Application
from Transient Flight Data. TN of the Solutions Obtained in the First
2370, June 1951. Partial Report to Tab-Controlled Air-
planes. TM 1198, September 1949.

CONTROL Dods, Jules B., Jr.: Wind-Tunnel Inves-
tigation of Horizontal Tails. V -
(1.8.2) 450 Swept-Back Plan Form of Aspect
Ratio 2. RM A9D05, September 1949.
Wilson, Herbert A., Jr. and Lovell,
J. Calvin: Full-Scale Investigation Gustafson, F. B.; Amer, Kenneth B.;
of the Maximum Lift and Flow Char- Haig, C. R.; and Reeder, J. P.:
acteristics of an Airplane having Longitudinal Flying Cualities of
Approximately Triangular Plan Several Single-Rotor Helicopters
Form. RM L6K20, February 1947. in Forward Flight. TN 1983, Novem-
ber 1949.
Klinar, Walter J. and Wilson, Jack H. :
Spin-Tunnel Investigation of the Ef- Lange, Roy H. and McLemore, Huel C.:
fects of Mass and Dimensional Vari- Static Longitudinal Stability and Con-
ations on the Spinning Characteris- trol of a Convertible-Type Airplane
tics of a Low-Wing Single-Vertical- as Affected by Articulated- and Rigid-
Tail Model Typical of Personal- Propeller Operation. TN 2014, Feb-
Owner Airplanes. TN 2352, May ruary 1950.
1951.







AERODYNAMICS
72 STABILITY AND CONTROL (1.8)

Longitudinal Control (Cont.) Tucker, Warren A. and Nelson, Robert L.:
The Effect of Torsional Flexibility on
Matheny, Cloyce E.: Maximum Pitch- the Rolling Characteristics at Super-
ing Angular Accelerations of Air- sonic Speeds of Tapered Unswept
planes Measured in Flight. TN Wings. Rept. 972, 1950.
2103, May 1950.
Bird, John D. and Jaquet, Byron M.: A
Mathews, Charles W.; Talmage, Study of the Use of Experimental
Donald B. ; and Whitten, James B.: Stability Derivatives in the Calcula-
Effects of Longitudinal Stability tion of the Lateral Disturbed Mo-
and Control Characteristics of a tions of a Swept-Wing Airplane and
B-29 Airplane of Variations in Comparison with Flight Results.
Stick-Force and Control-Rate TN 2013, January 1950.
Characteristics Obtained through
Use of a Booster in the Elevator- Lovell, Powell M., Jr. and Stassi,
Control System. TN 2238, Febru- Paul P.: A Comparison of the
ary 1951. Lateral Controllability with Flap
and Plug Ailerons on a Sweptback-
Dods, Jules B., Jr.: Estimation of Wing Model. TN 2089, May 1950.
Low-Speed Lift and Hinge-Moment
Parameters for Full-Span Trailing- DeYoung, John: Theoretical Antisym-
Edge Flaps on Lifting Surfaces with metric Span Loading for Wings of
and without Sweepback. TN 2288, Arbitrary Plan Form at Subsonic
February 1951. Speeds. TN 2140, July 1950.

LATERAL CONTROL Johnson, Harold S. and Hagerman,
(1.8.2.2) John R.: Wind-Tunnel Investigation
at Low Speed of the Lateral Control
Toll, Thomas A.: Summary of Lateral- Characteristics of an Unswept Un-
Control Research. Rept. 868, 1947. tapered Semispan Wing of Aspect
Ratio 3.13 Equipped with Various
Sawyer, Richard H.: Flight Measure- 25-Percent-Chord Plain Ailerons.
ments of the Lateral Control Char- TN 2199, October 1950.
acteristics of Narrow-Chord
Ailerons on the Trailing Edge of Hassell, James L. and Bennett,
a Full-Span Slotted Flap. Rept. Charles V.: The Dynamic Lateral
883, 1947. Control Characteristics of Airplane
Models having Unswept Wings with
Purser, Paul E. and Spearman, Round- and Sharp-Leading-Edge
M. Leroy: Wind-Tunnel Tests at Sections. TN 2219, November 1950.
Low Speed of Swept and Yawed Wings
having Various Plan Forms. RM Riebe, John M. and Watson, James M.:
L7D23, May 1947. The Effect of End Plates on Swept
Wings at Low Speed. TN 2229,
Phillips, William H.: Appreciation and November 1950.
Prediction of Flying Qualities.
Rept. 927, 1949. Lovell, Powell M., Jr.: A Comparison
of the Lateral Controllability with
Tucker, Warren A. and Nelson, Robert L: Flap and Plug Ailerons on a Sweptback-
Theoretical Characteristics in Su- Wing Model having Full-Span Flaps.
personic Flow of Two Types of TN 2247, December 1950.
Control Surfaces on Triangular
Wings. Rept. 939, 1949. Adams, Gaynor J.: Theoretical Damping
in Roll and Rolling Effectiveness of
Faber, Stanley: Comparison of Effective- Slender Cruciform Wings. TN 2270,
ness of Coordinated Turns and Level January 1951.
Sideslips for Correcting Lateral
Displacement during Landing Ap-
proaches. RM L9I29, December
1949.








AERODYNAMICS
STABILITY AND CONTROL (1.8) 73

Lateral Control (Cont.) Bird, John D. and Jaquet, Byron M. : A
Study of the Use of Experimental
Sivells, James C. and Westrick, Stability Derivatives in the Calcula-
Gertrude C.: Method for Calculat- tion of the Lateral Disturbed Mo-
ing Lift Distributions for Unswept tions of a Swept-Wing Airplane and
Wings with Flaps or Ailerons by Comparison with Flight Results.
Use of Nonlinear Section Lift Data. TN 2013, January 1950.
TN 2283, January 1951.
Hassell, James L. and Bennett,
Hewes, Donald E.: The Effects of Mass Charles V.: The Dynamic Lateral
Distribution on the Low-Speed Dy- Control Characteristics of Airplane
namic Lateral Stability and Control Models having Unswept Wings with
Characteristics of a Model with a Round- and Sharp-Leading-Edge
450 Sweptback Wing. TN 2313, Sections. TN 2219, November 1950.
March 1951.
Dods, Jules B., Jr.: Estimation of Low-
Johnson, Harold S. and Hagerman, Speed Lift and Hinge-Moment Param-
John R.: Wind-Tunnel Investigation eters for Full-Span Trailing-Edge
at Low Speed of Lateral Control Flaps on Lifting Surfaces with and
Characteristics of an Untapered without Sweepback. TN 2288, Febru-
450 Sweptback Semispan Wing of ary 1951.
Aspect Ratio 1. 59 Equipped with
Various 25-Percent-Chord Plain Hewes, Donald E. : The Effects of Mass
Ailerons. TN 2316, March 1951. Distribution on the Low-Speed Dy-
namic Lateral Stability and Control
Fischel, Jack and Hagerman, John R.: Characteristics of a Model with a
Effect of Aspect Ratio and Sweep- 450 Sweptback Wing. TN 2313,
back on the Low-Speed Lateral March 1951.
Control Characteristics of Un-
tapered Low-Aspect-Ratio Wings AIR BRAKES
Equipped with Retractable Ailerons. (1.8.2.4)
TN 2347, May 1951.
Stephenson, Jack D.: The Effects of
Naeseth, Rodger L. and O'Hare, Aerodynamic Brakes upon the
William M.: Effect of Aspect Ratio Speed Characteristics of Airplanes.
on the Low-Speed Lateral Control TN 1939, September 1949.
Characteristics of Unswept Un-
tapered Low-Aspect-Ratio Wings. HINGE MOMENTS
TN 2348, May 1951. (1.8.2.5)

DIRECTIONAL CONTROL Phillips, William H.: Appreciation and
(1.8.2.3) Prediction of Flying Cualities.
Rept. 927, 1949.
Phillips, William H.: Appreciation and
Prediction of Flying Qualities. Tucker, Warren A. and Nelson, Robert L.:
Rept. 927, 1949. Theoretical Characteristics in Super-
sonic Flow of Two Types of Control
Dods, Jules B., Jr.: Wind Tunnel In- Surfaces on Triangular Wings. Rept.
vestigation of Horizontal Tails. V 939, 1949.
450 Swept-Back Plan Form of As-
pect Ratio 2. RM A9D05, Septem-
ber 1949.







AERODYNAMICS
74 STABILITY AND CONTROL (1.8)

Hint;e '.oments Control (Cont.) Johnson, Harold S. and Hagerman,
John R.: Wind-Tunnel Investigation
Dods, Jules B., Jr.: Wind-Tunnel In- at Low Speed of Lateral Control
vestigation of Horizontal Tails. V Characteristics of an Untapered
450 Swept-Back Plan Form of As- 450 Sweptback Semispan Wing of
pect Ratio 2. RM A9D05, Septem- Aspect Ratio 1. 59 Equipped with
ber 1949. Various 25-Percent-Chord Plain
Ailerons. TN 2316, March 1951.
Bihrle, William, Jr.: Floating Charac-
teristics of Rudders and Elevators Bihrle, William, Jr.: Floating Char-
in Spinning Attitudes as Determined acteristics of a Plain and a Horn-
from Ilinge-Moment-Coefficient Balanced Rudder at Spinning Atti-
Data with Application to Personal- tudes as Determined from Rotary
Owner-Type Airplanes. TN 2016, Tests on a Model of a Typical Low-
January 1950. Wing Personal-Owner Airplane.
TN 2359, May 1951.
Johnson, Harold S. and HIagerman,
John R.: Wind-Tunnel Investigation AUTOMATIC CONTROL
at Low Speed of an Unswept Un- (1.8.2.6)
tapered Semispan Wing of Aspect
Ratio 3. 13 Equipped with Various Fliigge-Lotz, I. and Klotter, K.: On
25-Percent-Chord Plain Flaps. the Motions of an Oscillating System
TN 2080, April 1950. under the Influence of Flip-Flop
Controls. TM 1237, November
Johnson, Harold S. and IIagerman, 1949.
John R.: Wind-Tunnel Investigation
at Low Speed of a 450 Sweptback Un- Curfman, Howard J., Jr. and Gardiner,
tapered Semispan Wing of Aspect Robert A. : Method for Determining
Ratio 1. 59 Equipped with Various the Frequency-Response Character-
25-Percent-Chord Plain Flaps. istics of an Element or System from
TN 2169, August 1950. the System Transient Output Response
to a Known Input Function. Rept.
Stough, Carl J. and Kauffman, 984, 1950.
William M.: A Flight Investigation
and Analysis of the Lateral- Gardiner, Robert A.; Zarovsky, Jacob;
Oscillation Characteristics of an and Ankenbruck, H. O.: An Investi-
Airplane. TN 2195, October 1950. gation of the Stability of a System
Composed of a Subsonic Canard Air-
Johnson, Harold S. and Hagerman, frame and a Canted-Axis Gyroscope
John R. : Wind-Tunnel Investigation Automatic Pilot. TN 2004, January
at Low Speed of the Lateral Control 1950.
Characteristics of an Unswept Un-
tapered Semispan Wing of Aspect Beckhardt, Arnold R.: A Theoretical In-
Ratio 3.13 Equipped with Various vestigation of the Effect on the
25-Percent-Chord Plain Ailerons. Lateral Oscillations of an Airplane
TN 2199, October 1950. of an Automatic Control Sensitive
to Yawing Accelerations. TN 2006,
Dods, Jules B., Jr.: Estimation of January 1950.
Low-Speed Lift and Hinge-Moment
Parameters for Full-Span Trailing- Sponder, E. W. : Investigations of
Edge Flaps on Lifting Surfaces with Lateral Stability of a Glide Bomb
and without Sweepback. TN 2288, Using Automatic Control having
February 1951. no Time Lag. TM 1248, August
1950.








AERODYNAMICS
STABILITY AND CONTROL (1.8) 75

Automatic Control (Cont.) Stone, Ralph W., Jr.; Burk, Sanger M.,
Jr.; and Bihrle, William, Jr.:
Smaus, Louis H. and Stewart, The Aerodynamic Forces and Mo-
Elwood C.: Practical Methods of ments on a 1/10-Scale Model of a
Calculation Involved in the Experi- Fighter Airplane in Spinning Attidues
mental Study of an Autopilot and the as Measured on a Rotary Balance in
Autopilot-Aircraft Combination. the Langley 20-Foot Free-Spinning
TN 2373, June 1951. Tunnel. TN 2181, September 1950.

Turner, Howard L.: Measurement of
SPINNING the Moments of Inertia of an Air-
plane by a Simplified Method. TN
(1.8.3) 2201, October 1950.

Berman, Theodore: Spin-Tunnel Inves- Klinar, Walter J. and Wilson, Jack II.:
tigation d the Jettisoning of External Spin-Tunnel Investigation of the
Fuel Tanks in Spins. RM L9J25, Effects of Mass and Dimensional
November 1949. Variations on the Spinning Char-
acteristics of a Low-Wing Single-
Kohler, M. and Mautz, W.: Pressure- Vertical-Tail Model Typical of
Distribution Measurements on the Personal-Owner Airplanes. TN
Tail Surfaces of a Rotating Model 2352, May 1951.
of the Design BFW M 31. TM
1220, December 1949. Bihrle, William, Jr.: Floating Char-
acteristics of a Plain and a Horn-
Bihrle, William, Jr.: Floating Charac- Balanced Rudder at Spinning Atti-
teristics of Rudders and Elevators tudes as Determined from Rotary
in Spinning Attitudes as Determined Tests on a Model of a Typical
from Hinge-Moment-Coefficient Low-Wing Personal-Owner Air-
Data with Application to Personal- plane. TN 2359, May 1951.
Owner-Type Airplanes. TN 2016,
January 1950. STALLING
STALLING
Jones, Ira P., Jr. and Klinar, Walter J.:
Spin-Tunnel Investigation to Deter- (1.8.4)
mine the Effect on Spin Recoveries
of Reducing the Opening Shock Load Purser, Paul E. and Spearman,
of Spin-Recovery Parachutes. TN M. Leroy: Wind-Tunnel Tests at
2051, March 1950. Low Speed of Swept and Yawed
Wings having Various Plan Forms.
Huffschmid, A. : Investigation of the RM L7D23, May 1947.
Model ME 210 in the Spin Wind Tun-
nel of the DVL Fourth Partial Phillips, William H. : Appreciation
Report Model with a Vee Tail. and Prediction of Flying Qualities.
TM 1222, April 1950. Rept. 927, 1949.

Scher, Stanley H. and Draper, John W.: Sivells, James C. and Spooner,
The Effects of Stability of Spin- Stanley : Investigation in the
Recovery Tail Parachutes on the Langley 19-Foot Pressure Tun-
Behavior of Airplanes in Gliding nel of Two Wings of NACA 65-210
Flight and in Spins. TN 2098, and 64-210 Airfoil Sections with
May 1950. Various Type Flaps. Rept. 942,
1949.
Berman, Theodore: Comparison of
Model and Full-Scale Spin Test Re-
sults for 60 Airplane Designs. TN
2134, July 1950.







AERODYNAMICS
76 STABILITY AND CONTROL (1.8)

Stalling (:ont.) Kauffman, William M.; Liddell,
Charles J., Jr.; Smith, Allan; and
Aiken, William S., Jr. and Howard, Van Dyke, Rudolph D., Jr.: An
Donald A.: A Comparison of Wing Apparatus for Varying Effective
Loads Measured in Flight on a Dihedral in Flight with Application
Fighter-Type Airplane by Strain- to a Study of Tolerable Dihedral on
Gage and Pressure-Distribution a Conventional Fighter Airplane.
Methods. TN 1967, November 1949. Rept. 948, 1949.

Harper, Paul W. and Flanigan, Roy E.: Lovell, J. Calvin and Lipson, Stanley.
The Effect of Rate of Change of An Analysis of the Effect of Lift-
Angle of Attack on the Maximum Drag Ratio and Stalling Speed on
Lift of a Small Model. TN 2061, Landing-Flare Characteristics.
March 1950. TN 1930, September 1949.

Rose, Leonard M. and Altman, John M.: Gustafson, F. B.; Amer, Kenneth B.;
Low-Speed Investigation of the Haig, C. R.; and Reeder, J. P.:
Stalling of a Thin, Faired, Double- Longitudinal Flying Qualities of
Wedge Airfoil with Nose Flap. TN Several Single-Rotor Helicopters
2172, August 1950. in Forward Flight. TN 1983,
November 1949.
Kelly, John A.: Effects of Modifications
to the Leading-Edge Region on the Faber, Stanley: Comparison of Effective-
Stalling Characteristics of the NACA ness of Coordinated Turns and Level
631-012 Airfoil Section. TN 2228, Sideslips for Correcting Lateral
November 1950. Displacement during Landing Ap-
proaches. RM L9129, December
Peterson, Robert F.: The Boundary- 1949.
Layer and Stalling Characteristics
of the NACA 64A010 Airfoil Sec- Johnson, Harold I.: Flight Investigation
tion. TN 2235, November 1950. of the Effect of Various Vertical-
Tail Modifications on the Directional
Sivells, James C. and Westrick, Stability and Control Characteristics
Gertrude C.: Method for Calcula- of a Propeller-Driven Fighter Air-
ting Lift Distributions for Unswept plane. Rept. 973, 1950.
Wings with Flaps or Ailerons by
Use of Nonlinear Section Lift Data. Bird, John D. and Jaquet, Byron M.: A
TN 2283, January 1951. Study of the Use of Experimental
Stability Derivatives in the Calcula-
tion of the Lateral Disturbed Motions
FLYING QUALITIES of a Swept-Wing Airplane and
(1 .) Comparison with Flight Results.
.8.5 TN 2013, January 1950.

Phillips, William H.: Appreciation and Stiiper: Flight Experiences and Tests on
Prediction of Flying Qualities. Two Airplanes with Suction Slots.
Rept. 927, 1949. TM 1232, January 1950.

Matheny, Cloyce E.: Maximum Pitching
Angular Accelerations of Airplanes
Measured in Flight. TN 2103, May
1950.








AERODYNAMICS
STABILITY AND CONTROL (1.8) 77

Flying '.ualities (Cont.) Stone, Ralph W., Jr.; Burk, Sanger M.,
Jr.; and Bihrle, William, Jr.: The
Talmage, Donald B.; Reeder, John P.; Aerodynamic Forces and Moments
and Matthews, Ruth G.: Flight In- on a 1/10-Scale Model of a Fighter
vestigation of Longitudinal Stability Airplane in Spinning Attitudes as
and Control Characteristics and Measured on a Rotary Balance in
Stalling Characteristics of a C-54D the Langley 20-Foot Free-Spinning
Airplane. RM L9L21, May 1950. Tunnel. TN 2181, September 1950.

Amer, Kenneth B.: Theory of Helicopter Turner, Howard L.: Measurement of
Damping in Pitch or Roll and a the Moments of Inertia of an Air-
Comparison with Flight Measure- plane by a Simplified Method. TN
ments. TN 2136, October 1950. 2201, October 1950.

Stough, Carl J. and Kauffman, William M.: Hewes, Donald E.: The Effects of Mass
A Flight Investigation and Analysis of Distributions on the Low-Speed Dy-
the Lateral-Oscillation Characteris- namic Lateral Stability and Control
tics of an Airplane. TN 2195, Octo- Characteristics of a Model with a
ber 1950. 450 Sweptback Wing. TN 2313,
March 1951.
Mathews, Charles W.; Talmage,
Donald B.; and Whitten, James B.: Klinar, Walter J. and Wilson, Jack H.:
Effects on Longitudinal Stability and Spin-Tunnel Investigation of the Ef-
Control Characteristics of a B-29 fects of Mass and Dimensional
Airplane of Variations in Stick- Variations on the Spinning Charac-
Force and Control-Rate Character- teristics of a Low-Wing Single-
istics Obtained through Use of a Vertical-Tail Model Typical of
Booster in the Elevator-Control Personal-Owner Airplanes. TN
System. TN 2238, February 1951. 2352, May 1951.

Hewes, Donald E.: The Effects of Mass
Distribution on the Low-Speed Dy- AUTOMATIC STABILIZATION
namic Lateral Stability and Control ( )
Characteristics of a Model with a \1.8.8)
450 Sweptback Wing. TN 2313,
March 1951. Fligge-Lotz, I. and Klotter, K.: On the
Motions of an Oscillating System
MASS AND under the Influence of Flip-Flop
Controls. TM 1237, November
GYROSCOPIC PROBLEMS 1949.

(1.8.6)
1.8.6 Gardiner, Robert A.; Zarovsky, Jacob;
Neihouse, Anshal I. and Pepoon, and Ankenbruck, H. O. : An Investi-
Philip W.: Dynamic Similitude be- gation of the Stability of a System
tween a Model and a Full-Scale Composed of a Subsonic Canard
Body for Model Investigation at Airframe and a Canted-Axis Gyro-
Full-Scale Mach Number. TN scope Automatic Pilot. TN 2004,
2062, March 1950. January 1950.

Sponder, E. W. : Investigation of Sternfield, Leonard and Gates,
Lateral Stability of a Glide Bomb Ordway B., Jr.: A Theoretical
Using Automatic Control having Analysis of the Effect of Time Lag
no Time Lag. TM 1248, August in an Automatic Stabilization Sys-
1950. tem on the Lateral Oscillatory
Stability of an Airplane. TN 2005,
January 1950.







AERODYNAMICS
78 STABILITY AND CONTROL (1.8)

Automatic Stabilization (Cont.)

Sponder, E. W.: Investigations of
Lateral Stability of a Glide Bomb
Using Automatic Control having
no Time Lag. TM 1248, August
1950.

Jones, Arthur L. and Briggs,
Benjamin R.: A Survey of Stability
Analysis Techniques for Auto-
matically Controlled Aircraft.
TN 2275, January 1951.

Gates, Ordway B., Jr. and Schy,
Albert A.: A Theoretical Method
of Determining the Control Gearing
and Time Lag Necessary for a
Specified Damping of an Aircraft
Equipped with a Constant-Time-
Lag Autopilot. TN 2307, March
1951.

Smaus, Louis H. and Stewart, Elwood C.:
Practical Methods of Calculation
Involved in the Experimental Study
of an Autopilot and the Autopilot-
Aircraft Combination. TN 2373,
June 1951.







AERODYNAMICS 79




Aeroelasticity

(1.9)


Skoog, Richard B. and Brown, Harvey H.:
A Method for the Determination of
the Spanwise Load Distribution of a
Flexible Swept Wing at Subsonic
Speeds. TN 2222, March 1951.







80 AERODYNAMICS





Parachutes

(uo)


Jones, Ira P., Jr. and Klinar, Walter J.:
Spin-Tunnel Investigation to Deter-
mine the Effect on Spin Recoveries
of Reducing the Opening Shock Load
of Spin-Recovery Parachutes. TN
2051, March 1950.

Scher, Stanley H. and Draper, John W.:
The Effects of Stability of Spin-
Recovery Tail Parachutes on the
Behavior of Airplanes in Gliding
Flight and in Spins. TN 2098,
May 1950.

B. "mby, J. G. ; Cunningham, H. J.;
and Garrick, I. E.: Study of Ef-
fects of Sweep on the Flutter of
Cantilever Wings. TN 2121, June
1950.

Berman, Theodore: Comparison of
Model and Full-Scale Spin Test
Results for 60 Airplane Designs.
TN 2134, July 1950.















HYDRODYNAMICS
(2).










HYDRODYNAMICS 81




Theory

(2.1)


Imlay, Frederick H.: Theoretical Mo-
tions of Hydrofoil Systems. Rept.
918, 1948.
Sokolov, N. A.: Hydrodynamic Prop-
erties of Planing Surfaces and Fly-
ing Boats. TM 1246, October 1950.







82 HYDRODYNAMICS




General Arrangement Studies

(2.2)


Olson, Roland E. and Land, Norman S.:
Effect of Afterbody Length and Keel
Angle on Minimum Depth of Step
for Landing Stability and on Take-
Off Stability of a Flying Boat.
Rept. 923, 1949.

Kapryan, Walter J.: Effect of Forebody
Warp and Increase in Afterbody
Length on the Hydrodynamic Quali-
ties of a Flying-Boat Hull of High
Length-Beam Ratio. TN 1980,
November 1949.

Whitaker, Walter E., Jr. and Bryce,
Paul W., Jr. : Effect of an Increase
in Angle of Dead Rise on the Hydro-
dynamic Characteristics of a High-
Length-Beam-Ratio Hull. TN
2297, February 1951.







HYDRODYNAMICS 83







Seaplane Hull Variables

(2.3)


LENGTH-BEAM RATIO DEADRISE

(2.3.1) (2.3.2)

Kapryan, Walter J.: Effect of Forebody Kapryan, Walter J.: Effect of Forebody
Warp and Increase in Afterbody Warp and Increase in Afterbody
Length on the Hydrodynamic Quali- Length on the Hydrodynamic Quali-
ties of a Flying-Boat Hull of High ties of a Flying-Boat Tull of High
Length-Beam Ratio. TN 1980, Length-Beam Ratio. TN 1980,
November 1949. November 1949.

Sottorf, W. : Systematic Model Re- Sottorf, W.: Systematic Model Re-
searches on the Stability Limits of searches on the Stability Limit s of
the DVL Series of Float Designs. the DVL Series of Float Designs.
TM 1254, December 1949. TM 1254, December 1949.

Batterson, Sidney A. and McArver, Smiley, Robert F.: A Study of Water
A. Ethelda: Water Landing Inves- Pressure Distributions during
tigation of a Model having a Heavy Landings with Special Reference to
Beam Loading and a 300 Angle of a Prismatic Model having a Heavy
Dead Rise. TN 2015, February Beam Loading and a 300 Angle of
1950. Dead Rise. TN 2111, July 1950.

Smiley, Robert F.: A Study of Water Whitaker, Walter E., Jr. and Bryce,
Pressure Distributions during Paul W., Jr. : Effect of an Increase
Landings with Special Reference in Angle of Dead Rise on the Hydro-
to a Prismatic Model having a dynanic Characteristics of a High-
Heavy Beam Loading and a 300 Length-Beam-Ratio Hull. TN 2297,
Angle of Dead Rise. TN 2111, February 1951.
July 1950.

Whitaker, Walter E., Jr. and Bryce, STEPS
Paul W., Jr.: Effect of an Increase
in Angle of Dead Rise on the Hydro- (2.3.3)
dynamic Characteristics of a High-
Length-Beam-Ratio Hull. TN 2297, Olson, Roland E. and Land, Norman S.:
February 1951. Effect of Afterbody Length and Keel
Angle on Minimum Depth of Step for
McArver, A. Ethelda: Water-Landing Landing Stability and on Take-Off
Investigation of a Model having Stability of a Flying Boat. Rept.
Heavy Beam Loadings and 00 Angle 923, 1949.
of Dead Rise. TN 2330, April 1951.






HYDRODYNAMICS
84 SEAPLANE HULL VARIABLES (2.3)

Steps (Cont.) CHINES
Ferguson, J. A.; Seibels, R. E., Jr.;
and Corber, R. J.: Flight Tests 2.3.6)
of the Hydrodynamic Characteris-
tics of a Japanese "Emily" Flying Smiley, Robert F.: A Study of Water
Boat. TN 1968, September 1949. Pressure Distributions during
Landings with Special Reference
Sottorf, W.: Systematic Model Re- to a Prismatic Model having a
searches-on the Stability Limits Heavy Beam Loading and a 300
of the DVL Series of Float Designs. Angle of Dead Rise. TN 2111,
TM 1254, December 1949. July 1950.


AFTERBODY SHAPE

(2.3.4)

Olson, Roland E. and Land, Norman S.:
Effect of Afterbody Length and Keel
Angle on Minimum Depth of Step
for Landing Stability and on Take-
Off Stability of a Flying Boat.
Rept. 923, 1949.

Kapryan, Walter J.: Effect of Forebody
Warp and Increase in Afterbody
Length on the Hydrodynamic Quali-
ties of a Flying-Boat Hull of High
Length-Beam Ratio. TN 1980
November 1949.

Sottorf, W.: Systematic Model Re-
searches on the Stability Limits
of the DVL Series of Float Designs.
TM 1254, December 1949.

FOREBODY SHAPE

(2.3.5)

Milwitzky, Benjamin: A Theoretical
Investigation of Hydrodynamic
Impact Loads on Scalloped-Bottom
Seaplanes and Comparisons with
Experiment. Rept. 867, 1947.

Ferguson, J. A.; Seibels, R. E., Jr.;
and Corber, R. J.: Flight Tests
of the Hydrodynamic Characteris-
tics of a Japanese "Emily" Flying
Boat. TN 1968, September 1949.

Sottorf, W.: Systematic Model Re-
searches on the Stability Limits
of the DVL Series of Float Designs.
TM 1254, December 1949.







HYDRODYNAMICS 85




Specific Seaplanes and Hulls

(2.4)

Ferguson, J. A.; Seibels, R. E., Jr.;
and Corber, R. J.: Flight Tests of
the Hydrodynamic Characteristics
of a Japanese "Emily" Flying Boat.
TN 1968, September 1949.






86 HYDRODYNAMICS




Planing Surfaces

(2.6)


Milwitzky, Benjamin: A Theoretical
Investigation of Hydrodynamic Im-
pact Loads on Scalloped-Bottom
Seaplanes and Comparisons with
Experiment. Rept. 867, 1947.

Sottorf, W.: Systematic Model Re-
searches on the Stability Limits
of the DVL Series of Float Designs.
TM 1254, December 1949.

Sokolov, N. A.: Hydrodynamic Proper-
ties of Planing Surfaces and Flying
Boat. TM 1246, October 1950.

Tillmann, vV.: Additional Measurements
of the Drag of Surface Irregularities
in Turbulent Boundary Layers. TM
1299, January 1951.






HYDRODYNAMICS 87



Hydrofoils

(2.7)

Imlay, Frederick H.: Theoretical Mo-
tions of Hydrofoil Systems. Rept.
918, 1948.






88 HYDRODYNAMICS




Surface Craft

(2.8)


Imlay, Frederick H.: Theoretical Mo-
tions of Hydrofoil Systems. Rept.
918, 1948.

Kapryan, Walter J.: Effect of Forebody
Warp and Increase in Afterbody
Length on the Hydrodynamic Quali-
ties of a Flying-Boat Hull of High
Length-Beam Ratio. TN 1980,
November 1949.







HYDRODYNAMICS 89




Ditching Characteristics

(2.9)


Sottorf, W.: Landing Procedure in
Model Ditching Tests of Bf 109.
TM 1247, December 1949.

Fisher, Lloyd J. and Morris, Garland J.:
Ditching Tests of a 1/18-Scale Model
of the Lockheed Constellation Air-
plane. RM L8K18, April 1950.

Fisher, Lloyd J. and Hoffman,
Edward L.: Model Ditching Investi-
gation of the Douglas DC-4 and
DC-6 Airplanes. RM L9KO2a,
May 1950.