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- 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
- Characteristics of the Langley 8-foot transonic tunnel with slotted test section
- Compressible laminar boundary layer over a yawed infinite cylinder with heat transfer and arbitrary Prandtl number
- Boron and zirconium from crucible refractories in a complex heat-resistant alloy
- Experimental determination of effects of frequency and amplitude on the lateral stability derivatives for a delta, a swept, and unswept wing oscillating in yaw
- Systematic two-dimensional cascade tests of NACA 65-series compressor blades at low speeds
- Free-Spinning-Tunnel Investigation of a 1/28-Scale Model of the North American FJ-4 Airplane with External Fuel Tanks, TED No. NACA AD 3112
- Investigation of Incipient Spin Characteristics of a 1/35-Scale Model of the Convair F-102A Airplane, Coord. No. AF-AM-79
- Theory of self-excited mechanical oscillations of helicopter rotors with hinged blades
- A wind-tunnel investigation of the aerodynamic characteristics of a full-scale supersonic-type three-blade propeller at Mach numbers to 0.96
- Theoretical analysis of total-pressure loss and airflow distribution for tubular turbojet combustors with constant annulus and liner cross-sectional areas
- Differential equations of motion for combined flapwise bending, chordwise bending, and torsion of twisted nonuniform rotor blades
- Ground simulator studies of the effects of valve friction, stick friction, flexibility, and backwash on power control system quality
- Blowing-type boundary-layer control as applied to the trailing-edge flaps of a 35 degree swept-wing airplane
- Flight measurements of the vibration experienced by a tandem helicopter in transition, vortex-ring state, landing, approach, and yawed flight
- A flight-test study of total-pressure distortion in a thick-lipped nose inlet