TRAIL - Technical Report Archive and Image Library

Effect of Taper Ratio on Lift, Drag, and Pitching-Moment Characteristics of Thin Wings of Aspect Ratio 3 With 53.1 Degrees Sweepback of Leading Edge at Subsonic and Supersonic Speeds

A Simplified Method for Calculating Aeroelastic Effects on the Roll of Aircraft

Behavior of the Bell X-1A Research Airplane During Exploratory Flights at Mach Numbers Near 2.0 and at Extreme Altitudes

Comparison of the Static Stability of a 68.7 Degree Delta-Wing Model with Dihedral and a Twisted and Cambered Wing Model of the Same Plan Form

Low-Speed Investigation of the Effects of Wing Tanks and Speed Brakes on the Static Stability of a Model Having a 40 Degree Swept Wing

Effect of Dissolved Oxygen on the Filterability of Jet Fuels for Temperatures Between 300 Degrees and 400 Degrees Fahrenheit

Note on Hovering Turns with Tandem Helicopters

Effects of Wing-Mounted Tank-Type Stores on the Low Lift Buffeting and Drag of a Swept-Wing Airplane Configuration Between Mach Numbers of 0.8 and 1.3

Flight Measurements of the Lateral Response Characteristics of the Convair XF-92A Delta-Wing Airplane

Flight Determination of the Longitudinal Stability and Control Characteristics of the Bell X-5 Research Airplane at 58.7 Degrees Sweepback

Experimental Investigation of a 0.4 Hub-Tip Diameter Ratio Axial-Flow Compressor Inlet Stage at Transonic Inlet Relative Mach Numbers 2: Stage and Blade-Element Performance

Investigation of Two Short Annular Diffuser Configurations Utilizing Section and Injection as a Means of Boundary-Layer Control

A Theoretical Investigation of a Compensating Network With Application to Roll Control Systems for Automatic Interceptors

Some Dielectric Properties of Suspensions of Boron Powders in Mineral Oil

Experimental Investigation at High Subsonic Speeds of the Rolling Stability Derivatives of a Complete Model with an Aspect-Ratio-2.52 Wing Having an Unswept 72-Percent-Chord Line and a High Horizontal tail

Performance of Pure Fuels in Single J33 Combustors 2: Hydrocarbon and Nonhydrocarbon Fuels

A Method for Studying the Transient Blade-Flapping Behavior of Lifting Rotors at Extreme Operating Conditions

Results of Measurements Made During the Approach and Landing of Seven High-Speed Research Airplanes

A Correlation of Airfoil Section Data with the Aerodynamic Loads Measured on a 45 Degree Sweptback Wing Model at Subsonic Mach Numbers

Effect of Design Compressor Pressure Ratio on Performance of Hypothetical Two-Spool Nuclear-Powered Turbojet Engines

Component Operating Trends During Acceleration and Deceleration of Two Hypothetical Two-Spool Turbojet Engines

Effect of Temperature on Viscosity of Slurries of Boron and Magnesium in JP-5 Fuel

Performance and Component Frontal Areas of a Hypothetical Two-Spool Turbojet Engine for Three Modes of Operation

Performance of a Tubular Turbojet Combustor at High Pressures and Temperatures

Comparative Dispersion Data From Ground-Launched 2.25-Inch Rockets Equipped With Cruciform and Monoplane Fins

Preliminary Evaluation of Flight-Weight XRJ47-W-5 Ram-Jet Engine at a Mach Number of 2.75

Performance of a Single Fuel-Vaporizing Combustor With Six Injectors Adapted for Gaseous Hydrogen

Flight Characteristics of a Wingless Rocket- Powered Model With Four Externally Mounted Air-to-Air Missiles at Mach Numbers 0.7 to 1.6

Experimental Investigation at High Subsonic Speeds of the Rolling-Stability Derivatives of a 1/22 Scale Model of the Republic F-105 Airplane

Some Effects of Aeroelasticity on the Rolling Effectiveness of a 10-Percent-Scale Model of the Mcdonnell F-101A Airplane Wing at Mach Numbers From 0.5 to 1.2

Some Effects of Roll Rate on the Longitudinal Stability Characteristics of the Hughes Falcon Missile, ''C'' Configuration, for a Mach Number Range of 1.1 to 1.8 as Determined From Flight Test

Static Longitudinal and Lateral Stability and Control Characteristics of an 0.065-Scale Model of the Chance Vought Regulus 2 Missile at Mach Numbers of 1.41, 1.61, and 2.01 Research Memorandum

Preliminary Free-Jet Performance of XRJ43-MA-3 Ram-Jet Engine at a Mach Number of 2.70

Summary and Analysis of Horizontal-Tail Contribution to Longitudinal Stability of Swept-Wing Airplanes at Low Speeds

Wind Tunnel Investigation at Low Speed of the Aerodynamic Characteristics of the Army Chemical Corps Model E112 Bomblets

Wing Pressure Distributions Over the Lift Range of the Convair XF-92A Delta-Wing Airplane at Subsonic and Transonic Speeds

Preliminary Results From Free-Jet Tests of a 48-Inch-Diameter Ram-Jet Combustor With an Annular Can-Type Flame Holder

Wind-Tunnel Measurements at Subsonic Speeds of the Static and Dynamic-Rotary Stability Derivatives of a Triangular-Wing Airplane Model Having a Triangular Vertical Tail

Effects of Various Modifications on the Static Longitudinal Stability and Control Characteristics of a 0.065-Scale Model of the Chance Vought Regulus II Missile at a Mach Number of 2.01

Effects of Free-Flight Rocket-Model Booster-Adapter Configurations on the Aerodynamic Characteristics in Pitch and Sideslip of a Swept-Wing Fighter Airplane Model at a Mach Number of 2.01

A Dye-Tracer Technique for Experimentally Obtaining Impingement Characteristics of Arbitrary Bodies and a Method for Determining Droplet Size Distribution

Low-Pressure Performance of a Tubular Combustor With Gaseous Hydrogen

Liquid Hydrogen as a Jet Fuel for High-Altitude Aircraft

A Low-Pressure-Loss Short Afterburner for Sea-Level Thrust Augmentation

Preliminary Results From Free-Jet Tests of a 48-Inch-Diameter Ram-Jet Combustor With an Annular-Piloted Baffle-Type Flameholder

Force and Pressure Measurements on Several Canopy-Fuselage Configurations at Mach Numbers 1.41 and 2.01

The Origin and Distribution of Supersonic Store Interference From Measurement of Individual Forces on Several Wing-Fuselagestore Configurations 1. - Swept-Wing Heavy-Bomber Configuration With Large Store (Nacelle). Lift and Drag; Mach Number, 1.61

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