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- A Method for Determining the Composition of Methanol-Trimethyl Borate Mixtures
- Summary of the Flight Conditions and Maneuvers in Which Maximum Wing and Tail Loads Were Experienced on a Swept-Wing Fighter Airplane
- A Theoretical Analysis of a Simple Aerodynamic Device to Improve the Longitudinal Damping of a Cruciform Missile Configuration at Supersonic Speeds
- 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