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Preliminary Investigation of the Transonic Characteristics of an NACA Submerged Inlet

Tabulated Pressure Coefficients and Aerodynamic Characteristics Measured on the Wing of the Bell X-1 Airplane in Level Flight at Mach Numbers From 0.79 to 1.00 and in a Pull-Up at a Mach Number of 0.96

A Transonic Wing Investigation in the Langley 8-Foot High-Speed Tunnel at High Subsonic Mach Numbers and at a Mach Number of 1.2 : Wing-Fuselage Configuration Having a Wing of 35 Degrees Sweepback, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Section

The Time Lag Between Flap Deflection and Force Development at a Mach Number of 4

Transonic Drag Characteristics of a Wing Body Combination Using a Thin Tapered Wing of 45 Degrees Sweepback

Propeller Section Aerodynamic Characteristics as Determined by Measuring the Section Surface Pressures on an NACA 10-(3)(08)-03 Propeller Under Operating Conditions

Results Obtained During Flights 1 to 6 of the Northrop X-4 Airplane (A.F. No. 46-677)

Summary of Normal Accelerations, Gust Velocities, and Operating Practices, From April to August 1949 of a Twin-Engine Airplane in Commercial Transport Operations

Rolling Effectiveness of a Thin Tapered Wing Having Partial-Span Ailerons as Determined by Rocket-Powered Test Vehicles

The Rolling Effectiveness of Wing-Tip Ailerons as Determined by Rocket-Powered Test Vehicles and Linear Supersonic Theory

Pressure Distributions on the Blade Sections of the NACA 10-(3)(066)-033 Propeller Under Operating Conditions

Pressure Distributions on the Blade Sections of the NACA 10-(5)(066)-03 Propeller Under Operating Conditions

Pressure Distributions on the Blade Sections of the NACA 10-(3)(049)-033 Propeller Under Operating Conditions

Pressure Distributions on the Blade Sections of the NACA 10-(0)(066)-03 Propeller Under Operating Conditions

Pressure Distributions on the Blade Sections of the NACA 10-(3)(090)-03 Propeller Under Operating Conditions

Pressure Measurements on a Sharply Converging Fuselage Afterbody With Jet on and Off at Mach Numbers From 0.8 to 1.6

Pressure-Rise and Leakage-Loss Characteristics of a Rotating Cowling

Spin-Tunnel Investigation of a Model of a 60 Degree Delta-Wing Airplane to Determine the Spin, Recovery, and Longitudinal Trim Characteristics Throughout an Extensive Range of Mass Loadings

Time Histories of Horizontal-Tail Loads, Elevator Loads, and Deformations on a Jet-Powered Bomber Airplane During Wind-Up Turns at Approximately 15,000 Feet and 22,500 Feet

Wind-Tunnel Investigation at Low Speed of a Wing Swept-Back 63 Degrees and Twisted and Cambered for a Uniform Load at a Lift Coefficient of 0.5

Wind-Tunnel Investigation at Low Speed of a Wing Swept Back 63 Degrees and Twisted and Cambered for Uniform Load at a Lift Coefficient of 0.5 and With a Thickened Tip Section

Wind-Tunnel Investigation of the Effects of a Jet Engine Nacelle on the Aerodynamic Characteristics of a 37.25 Degree Swept Back Wing at High Subsonic Speeds

Wind-Tunnel Investigation of the Low-Speed Longitudinal and Lateral Control Characteristics of a Triangular-Wing Model of Aspect Ratio 2.31 Having Constant-Chord Control Surfaces

The Use of Area Suction for the Purpose of Delaying Separation of Air Flow at the Leading Edge of a 63 Degree Swept-Back Wing

Theoretical Investigation of the Dynamic Lateral Stability Characteristics of the Douglas X-3 Research Airplane, Study 41-B

The Effect of Spanwise Aileron Location on the Rolling Effectiveness of Wings With 0 Degree and 45 Degree Sweep at Subsonic, Transonic, and Supersonic Speeds

The Effect of Sweepback on the Longitudinal Characteristics at a Mach Number of 1.24 of a 1/30 Scale Semispan Model of the Bell X-5 Airplane From Tests by the NACA Wing Flow Method

Effects of Varying the Size and Location of Trailing-Edge Flap-Type Controls on the Aerodynamic Characteristics of a Unswept Wing at a Mach Number of 1.9

Effects of Obstructions in Compressor Inlet on Blade Vibration in 10-Stage Axial-Flow Compressor

Effect of Compressibility and Camber as Determined From an Investigation of the NACA 4-(3)(08)-03 and 4-(5)(08)-03 Two-Blade Propellers Up to Forward Mach Numbers of 0.925

The Effect of Changes in the Leading-Edge Radius on the Aerodynamic Characteristics of a Symmetrical, 9-Percent-Thick Airfoil at High-Subsonic Mach Numbers

Determination by the Free-Fall Method of the Drag and Longitudinal Stability and Control Characteristics of a Canard Model at Transonic Speeds

Determination of Longitudinal Stability of the Bell X-1 Airplane From Transient Responses at Mach Numbers Up to 1.12 at Lift Coefficients of 0.3 and 0.6

Ditching Tests With a 1/16-Size Model of the Navy XP2V-1 Airplane at the Langley Tank No. 2 Monorail

Ditching Tests of a 1/18-Scale Model of the Lockheed Constellation Airplane

Drag Investigation of Some Fin Configurations for Booster Rockets at Mach Numbers Between 0.5 and 1.4

Calculated Lift Distributions of a Consolidated Vultee B-36 and Two Boeing B-47 Airplanes Coupled at the Wing Tips

The Calculation of the Path of a Jettisonable Nose Section

Damping in Yaw and Static Directional Stability of a Canard Airplane Model and of Several Models Having Fuselages of Relatively Flat Cross Section

The Damping in Roll of Rocket-Powered Test Vehicles Having Rectangular Wings With NACA 65-006 and Symmetrical Double-Wedge Airfoil Sections of Aspect Ratio 4.5

Aerodynamic Investigation of a Parabolic Body of Revolution at Mach Number of 1.92 and Some Effects of an Annular Jet Exhausting From the Base

Aerodynamic Characteristics at a Mach Number of 1.38 of Four Wings of Aspect Ratio 4 Having Quarter-Chord Sweep Angles of 0 Degrees, 35 Degrees, 45 Degrees, and 60 Degrees

Aerodynamic Characteristics at a Mach Number of 1.25 of a 6-Percent-Thick Triangular Wing and 6- and 9-Percent-Thick Triangular Wings in Combination With a Fuselage: Wing Aspect Ratio 2.31, Biconvex Airfoil Sections

Ability of Pilots to Control Simulated Short-Period Yawing Oscillations

Aerodynamic and Lateral-Control Characteristics of a 1/28-Scale Model of the Bell X-1 Airplane Wing-Fuselage Combination: Transonic-Bump Method

Altitude-Chamber Performance of British Rolls-Royce Nene II Engine 3 - 18.00-Inch-Diameter Jet Nozzle

Altitude Test Chamber Investigation of Performance of a 28-Inch Ram-Jet Engine 2: Effects of Gutter Width and Blocked Area on Operating Range and Combustion Efficiency

Altitude-Test-Chamber Investigation of Performance of a 28-Inch Ram-Jet Engine 1: Combustion and Operational Performance of Four Combustion-Chamber Configurations

Low-Speed Aerodynamic Characteristics of a Series of Swept Wings Having NACA 65A006 Airfoil Sections (Revised)

Maximum-Lift Investigation of a 1/40-Scale X-1 Airplane Wing at Mach Numbers From 0.60 to 1.15


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