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- Analysis of Rocket, Ram-Jet, and Turbojet Engines for Supersonic Propulsion of Long-Range Missiles 2 - Rocket Missile Performance
- Note on the Effects of First-Order Aerodynamic Loads on Propeller Shaft Loads with Emphasis on Counterrotating Propellers
- Preliminary Investigation of the Static Longitudinal and Lateral Stability Characteristics of a 0.05-Scale Model of the Convair F2Y-1 Airplane at High Subsonic Speeds
- High-Speed Drag and Opening Characteristics of a Kaman Rotochute Model
- Vapor pressures and calculated heats of vaporization of concentrated nitric acid solutions in the composition range 71 to 89 percent nitrogen dioxide, 1 to 10 percent water, and in the temperature range 10 to 60 degrees C
- A flight evaluation of the stability and control of the X-4 swept-wing semitailless airplane
- Flight determination of the drag of conical-shock nose inlets with various cowling shapes and axial positions of the center body at Mach numbers from 0.8 to 2.0
- Exploratory engine test of transpiration-cooled turbine-rotor blade with wire-cloth shell
- High-altitude performance of an experimental turbular prevaporizing combustor
- Investigation of impulse-type supersonic compressor with hub-tip ratio of 0.6 and turning to axial direction I : performance of rotor alone
- Investigation of a trailing-edge paddle-control surface on a triangular wing of aspect ratio 2 at subsonic and supersonic speeds
- Investigation of a supersonic-compressor rotor with turning to axial direction II : rotor component off-design and stage performance
- Investigation of a translating-cone inlet at Mach numbers from 1.5 to 2.0
- Internal performance at Mach number to 2.0 of two auxiliary inlets immersed in fuselage boundary layer
- Investigation of a high-temperature single-stage turbine suitable for air cooling and turbine stator adjustment 1: design of vortex turbine and performance with stator at design setting
- Investigation of a high-temperature single-stage turbine suitable for air cooling and turbine stator adjustment 2: performance of vortex turbine at various stator settings
- Investigation of a high-pressure ratio eight-stage axial-flow research compressor with two transonic inlet stages III : individual stage performance characteristics
- Investigation of a missile airframe with control surfaces consisting of projecting quadrants of the nose cone
- Investigation of a 10-stage subsonic axial-flow research compressor V : effect of reducing inlet-guide-vane turning on over-all and inlet-stage performance
- Investigation of a 10-stage subsonic axial-flow research compressor VI : performance evaluation and flow distributions in the first, fifth, and tenth stages
- An investigation of a supersonic aircraft configuration having a tapered wing with circular-arc sections and 40 degree sweepback : aerodynamic characteristics of the configuration equipped with a canard control surface at a Mach number of 1.89
- Investigation of Supersonic-Compressor Rotors Designed with External Compression
- Investigation of three highly loaded subsonic-inlet-stage axial-flow compressors employing varying radial gradients of energy addition
- Investigation of three low-temperature-ratio combustor configurations in a 48-inch-diameter ram-jet engine
- Investigation of transient combustion characteristics in a single tubular combustor
- Investigation to Mach number 2.0 of shock-positioning control systems for a variable-geometry inlet in combination with a J34 turbojet engine
- A method for increasing the effectiveness of stabilizing surfaces at high supersonic Mach numbers
- Method for studying helicopter longitudinal maneuver stability
- Thrust and pumping characteristics of a series of ejector-type exhaust nozzles at subsonic and supersonic flight speeds
- Pressure distributions on triangular and rectangular wings to high angles of attack Mach numbers 1.45 and 1.97
- Performance of isentropic nose inlets at Mach number of 5.6
- Performance of two air-cooled turbojet engines determined analytically from engine component performance for a range of cooling-air weight flows
- Performance of wedge-type boundary layer diverters for side inlets at supersonic speeds
- Optimum lifting bodies at high supersonic airspeeds
- Organophosphorus compounds in rocket-engine applications
- Performance of mixed-flow impeller, model MFI-1B, with diffuser vanes at equivalent impeller speeds from 1100 to 1700 feet per second
- Performance of five low-temperature-ratio ram-jet combustors over range of simulated altitudes
- Tests in the Ames 40- by 80-foot wind tunnel of the effects of varying wing modifications on the longitudinal characteristics of two-triangular wing airplane models with and without horizontal tails
- Matrix methods for determining the longitudinal-stability derivatives of an airplane from transient flight data
- Jet effects on pressure loading of all-movable horizontal stabilizer
- Wind pressure distributions at low lift for the XF-92A delta-wing airplane at transonic speeds
- Preliminary investigation of a technique for stability studies of a self-propelled model of a submerged submarine
- Preliminary investigation of an asymmetric swept nose inlet of circular projection at Mach number 3.85
- A preliminary study of the preparation of slurry fuels from vaporized magnesium
- Preliminary wind tunnel investigation of two types of jet-exit configurations for control of aircraft
- Preliminary investigation at subsonic and transonic speeds of the aerodynamic characteristics of a biplane composed of a sweptback and a sweptforward wing joined at the tips
- Preliminary drag measurements of the consolidated Vultee XF-92A delta-wing airplane in flight tests to a Mach number of 1.01
- Lift and drag characteristics of the Douglas X-3 research airplane obtained during demonstration flights to a Mach number of 1.20
- Lateral control characteristics of two structural similar flexible wings with 45 degrees sweep: a sweptback wing and a wing with M plan form
- Lift and drag characteristics of the Douglas D-558-II research airplane obtained in exploratory flights to a Mach number of 2.0