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- Abnormal grain growth in nickel-base heat-resistant alloys
- Abnormal grain growth in M-252 and S-816 alloys
- Experimental lift of low-aspect-ratio triangular wings at large angles of attack and supersonic speeds
- Performance of multiple jet-exit installations
- Ground reflection of jet noise
- Performance of basic XJ79-GE-1 turbojet engine and its components
- Simulator studies of jet reaction controls for use at high altitude
- Preliminary studies of rolling-contact fatigue life of high-temperature bearing materials
- Correlation of turbulent heat transfer in a tube for the dissociating system N204 reversibly yields 2N02
- Investigation at supersonic speeds of the compressor stall and inlet buzz characteristics of a J34 - spike-inlet combination
- Comparison of experimentally and analytically determined windmilling characteristics of a compressor with low over-all pressure ratio
- Preliminary results of the flight investigation between Mach numbers of 0.80 and 1.36 of a rocket-powered model of a supersonic airplane configuration having a tapered wing with circular-arc sections and 40©� sweepback
- Some measurements at subsonic speeds of the aerodynamic forces and moments on two delta wings of aspect ratios 2 and 4 oscillating about the midchord
- Investigation of fixed-geometry supersonic inlets with bypass ducts for matching turbojet-engine air-flow requirements over a range of transonic and supersonic speeds
- Effect at high subsonic speeds of fuselage forebody strakes on the static stability and vertical-tail-load characteristics of a complete model having a delta wing
- Surface pressure distributions on a large-scale 49©� sweptback wing-body-tail configuration with blowing applied over the flaps and wing leading edge
- Summary of locations, extents, and intensities of turbulent areas encountered during flight investigations of the jet stream from January 7, 1957 to April 28, 1957
- Heat transfer and pressure measurement on a 5-inch hemispherical concave nose at a Mach number of 2.0
- Preliminary investigation of the effects of several seeker-nose configurations on the longitudinal characteristics of a canard-type missile at a Mach number of 1.60
- Longitudinal characteristics of wings
- Recent design studies directed towards elimination of pitch-up
- An investigation of the drag characteristics of speed brakes for Mach numbers from 0.20 to 1.30
- Heat-transfer measurements in free flight at Mach numbers up to 14.6 on a flat-faced conical nose with a total angle of 29©�
- Effect of compressibility on the hovering performance of two 10-foot-diameter helicopter rotors tested in the Langley full-scale tunnel
- Simulation study of a high-performance aircraft including the effect on pilot control of large accelerations during exit and reentry flight
- Altitude Performance of the Afterburner on the Iroquois Turbojet Engine. Coord. No. AF-P-6
- Calculation of the Lateral Stability of a Directly Coupled Tandem-Towed Fighter Airplane and Correlation with Experimental Data
- Wind-Tunnel Investigation of the Low-Speed Characteristics of a 1/8-Scale Model of the Republic XP-91 Airplane with a Vee and a Conventional Tail. Addendum - Characteristics with a Revised Conventional Tail and Drooped Wing Tips
- Some Altitude Operational Characteristics of a Prototype Iroquois Turbojet Engine. COORD. NO. AF-P-6
- A tabulation of wind-tunnel pressure data at Mach numbers of 1.61 and 2.01 of five swept wings of the same plan form but different surface shapes
- Experimental Investigation of Flutter and Divergence Characteristics of the Rocket-Motor Fin of the ASROC Missile
- Investigation of Wingless Missile Configurations with Folding Controls and Low-Aspect-Ratio Stabilizing Surfaces
- Investigation of two bluff shapes in axial free flight over a Mach number range from 0.35 to 2.15
- A Body Modification to Reduce Drag Due to Wedge Angle of Wing with Unswept Trailing Edge
- Performance of an All-internal Conical Compression Inlet With Annular Throat Bleed at Mach Number 5.0
- Performance of an Inlet Having a Variable-angle Two-dimensional Compression Surface and a Fixed-geometry Subsonic Diffuser for Application to Reduced Engine Rotative Speeds- Mach Numbers 0.66, 1.5, 1.7, and 2.0
- NACA Conference on High-Speed Aerodynamics A compilation of papers presented
- Icing Frequencies Experienced During Climb and Descent by Fighter-Interceptor Aircraft
- Combustion of gaseous hydrogen at low pressures in a 35 degree sector of a 28-inch-diameter ramjet combustor
- Analysis of pressure distributions for a series of tip and trailing-edge controls on a 60 deg wing at Mach numbers of 1.61 and 2.01
- Boundary-Layer-Transition Measurements in Full-Scale Flight
- Effect of Pressure Level on Afterburner-wall Temperatures
- Exploratory wind-tunnel investigation to determine the lift effects of blowing over flaps from nacelles mounted above the wing
- Compatibility of Metals with Liquid Fluorine at High Pressures and Flow Velocities
- Supersonic Wave Interference Affecting Stability
- Application of the Method of Coordinate Perturbation to Unsteady Duct Flow
- Measurements of free-space oscillating pressures near propellers at flight Mach numbers to 0.72
- Turbulent Skin Friction at High Mach Numbers and Reynolds Numbers
- Drag minimization for wings and bodies in supersonic flow
- Calculated and measured stresses in simple panels subject to intense random acoustic loading including the near noise field of a turbojet engine