TRAIL - Technical Report Archive and Image Library

Wind-Tunnel Investigation at High and Low Subsonic Mach Numbers of a Thin Sweptback Wing Having an Airfoil Section Designed for High Maximum Lift

Wind-Tunnel Investigation at High Subsonic Speeds of Spoilers of Large Projection on an NACA 65A006 Wing With Quarter-Chord Line Swept Back 32.6 Degrees

A Wind-Tunnel Investigation at Low Speeds of the Aerodynamic Characteristics of Various Spoiler Configurations on a Thin 60 Degrees Delta Wing

Wind-Tunnel Investigation of the Low-Speed Static and Rotary Stability Derivatives of a 0.13-Scale Model of the Douglas D-558-II Airplane in the Landing Configuration

A Transonic Investigation of the Aerodynamic Characteristics of Plate- and Bell- Type Outlets for Auxiliary Air

Investigation of Effective Thermal Conductivities of Powders

Wind-Tunnel Investigation of the Static Lateral Stability Characteristics of Wing-Fuselage Combinations at High Subsonic Speeds: Sweep Series

A Theoretical Investigation of the Effect of a Target Seeker Sensitive to Pitch Attitude on the Dynamic Stability and Response Characteristics of a Supersonic Canard Missile Configuration

Thrust Loading of the NACA 3-(3)(05)-05 Eight-Blade Dual-Rotating Propeller as Determined From Wake Surveys

First Landing of Bell X-2 Research Airplane

The Effect of Surface Roughness on the Performance of a 23 Degree Conical Diffuser at Subsonic Mach Numbers

Evaluation of End- and Radial-Burning Solid Fuels in Ram Jets Mounted in a Free Jet at Mach Numbers of 2.0, 2.2, and 2.3

Effects of Chord Discontinuities and Chordwise Fences on Low-Speed Static Longitudinal Stability of an Airplane Model Having a 35 Degree Sweptback Wing

The Effects of Camber and Leading-Edge-Flap Deflection on the Pressure Pulsations on Thin Rigid Airfoils at Transonic Speeds

The Effect of Entrance Mach Number and Lip Shape on the Subsonic Characteristics of a Scoop-Type-Air-Induction System for a Supersonic Airplane

Effect of Fuselage Interference on the Damping in Roll of Delta Wings of Aspect Ratio 4 in the Mach Number Range Between 0.6 and 1.6 as Determined With Rocket Propelled Vehicles

Effect of Fuel-Air Distribution on Performance of a 16-Inch Ram-Jet Engine

Stability and Control Flight Tests of a 0.13-Scale Model of the Consolidated-Vultee XFY-1 Airplane in Take-Offs, Landings, and Hovering Flight: TED No. NACA DE 368

Comparison of Locked-Rotor and Windmilling Drag Characteristics of an Axial-Flow-Compressor Type Turbojet Engine

The Calculation of Certain Static Aeroelastic Phenomena of Wings With Tip Tanks or Boom-Mounted Lifting Surfaces

Calculation of Internal Pressures in the Fuel Tube of a Nuclear Reactor

Calibration of the Slotted Test Section of the Langley 8-Foot Transonic Tunnel and Preliminary Experimental Investigation of Boundary-Reflected Disturbances

Axial-Slot Air Admission for Controlling Performance of a One-Quarter-Annual Turbojet Combustor and Comparison With Complete Engine

Aerodynamic Characteristics of Two Delta Wings at Mach Number 4.04 and Correlations of Lift and Minimum-Drag Data for Delta Wings at Mach Numbers From 1.62 to 6.9

Aerodynamic Loading Characteristics of a Wing-Fuselage Combination Having a Wing of 45 Degrees Sweepback Measured in the Langley 8-Foot Transonic Tunnel

Aerodynamic Load Measurements Over a Leading-Edge Slat on a 40 Degree Sweptback Wing at Mach Numbers From 0.10 to 0.91

Aeronautical Characteristics of a 45 Degree Sweptback Wing-Fuselage Combination and the Fuselage Alone Obtained in the Langley 8-Foot Transonic Tunnel

Longitudinal Stability, Trim, and Drag Characteristics of a Rocket-Propelled Model of an Airplane Configuration Having a 45 Degree Sweptback Wing and an Unswept Horizontal Tail

Investigation of Interference, Lift, Drag, and Pitching Moment of a Series of Rectangular Wing and Body Combinations at Mach Numbers of 1.62, 1.93,and 2.41

Effect of Various Blade Modifications on Performance of a 16-Stage High-Pressure-Ratio Axial-Flow Compressor 1 - Effect on Over-All Performance Characteristics of Decreasing Twelfth Through Fifteenth State Stator-Blade Angles 3 Degrees

Effect of Various Blade Modifications on Performance of a 16-Stage Axial-Flow Compressor 2 - Effect on Over-All Performance Characteristics of Increasing Twelfth through Fifteenth Stage Stator-Blade Angles 3 Degrees

Effect of Various Blade Modifications on Performance of a 16-Stage Axial-Flow Compressor 5 - Effect on Over-All Performance Characteristics of a 20-Percent Reduction in Solidity of the Fourteenth Through Sixteenth Stage Rotors

Effect of Various Blade Modifications on Performance of a 16-Stage Axial-Flow Compressor 3 - Effect on Over-All Performance Characteristics on Increasing Stator-Blade Angles in Inlet Stages

Effect of Rotor- and Stator-Blade Modifications on Surge Performance of an 11-Stage Axial-Flow Compressor 1 - Original Production Compressor of XJ40-WE-6 Engine

Detailed Computational Procedure for Design of Cascade Blades With Prescribed Velocity Distributions in Compressible Potential Flows

Ditching Investigation of a 1/12-Scale Model of the Douglas F3D-2 Airplane, TED No. NACA DE 381

The Effect of an Operating Propeller on the Aerodynamic Characteristics of a 1/10-Scale Model of the Lockheed XFV-1 Airplane at High Subsonic Speeds (TED No. NACA DE-377)

Concerning the Flow About Ring-Shaped Cowlings Part 9: The Influence of Oblique Oncoming Flow on the Incremental Velocities and Air Forces at the Front Part of Circular Cowls

Amplitude of Supersonic Diffuser Flow Pulsations

Wind-Tunnel Investigation of the Static Longitudinal Stability Characteristics of a 0.15-Scale Model of the Hermes A-1E2 Missile at High Subsonic Mach Numbers

An Approximate Method of Calculating the Deformations of Wings Having Swept, M or W, A, and Swept-Tip Plan Forms

Some Experiences Regarding the Nonlinearity of Hot Wires

Small-Scale Transonic Investigation of the Effects of Partial-Span Leading-Edge Camber on the Aerodynamic Characteristics of a 50 Degree 38' Sweptback Wing of Aspect Ratio 2.98

Thirty-Seventh Annual Report of the National Advisory Committee for Aeronautics: Administrative Report Including Technical Report Nos. 1003 to 1058

Time-History Data of Maneuvers Performed by an F-86A Airplane During Squadron Operational Training

A method of calibrating airspeed installations on airplanes at transonic and supersonic speeds by the use of accelerometer and attitude-angle measurements

On Rotational Conical Flow

NACA 65-series compressor rotor performance with varying annulus-area ratio, solidity, blade angle, and Reynolds number and comparison with cascade results

A comparison of typical National Gas Turbine Establishment and NACA axial-flow compressor blade sections in cascade at low speed

Some notes on the aerodynamic loads associated with external-store installations

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