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- Formation and combustion of smoke in laminar flames
- Convection of a pattern of vorticity through a shock wave
- Low-Speed Longitudinal Stability and Lateral-Control Characteristics of a 0.3-Scale Model of the Republic RF-84F Airplane at a Reynolds Number of 9x10(exp 6)
- Effect of ground interference on the aerodynamic and flow characteristics of a 42 degree sweptback wing at Reynolds numbers up to 6.8 x 10(6)
- Exact solutions of laminar-boundary-layer equations with constant property values for porous wall with variable temperature
- A study of the characteristics of human-pilot control response to simulated aircraft lateral motions
- Structural response to discrete and continuous gusts of an airplane having wing bending flexibility and a correlation of calculated and flight results
- A visualization study of secondary flows in cascades
- Experimental investigation of acceleration characteristics of a turbojet engine including regions of surge and stall for control applications
- Comparison of performance of experimental and conventional cage designs and materials for 75-millimeter-bore cylindrical roller bearings at high speed
- Effects of sweep and thickness on the static longitudinal aerodynamic characteristics of a series of thin, low-aspect-ratio, highly tapered wings at transonic speeds: transonic-bump method
- Wind-tunnel investigation at low speed of the effects of chordwise wing fences and horizontal-tail position on the static longitudinal stability characteristics of an airplane model with a 35 degree sweptback wing
- Wind-Tunnel Investigation at Subsonic and Supersonic Speeds of a Fighter Model Employing a Low-aspect-ratio Unswept Wing and a Horizontal Tail Mounted Well above the Wing Plane - Lateral and Directional Stability
- Effect of a Leading-edge Flap upon the Lift, Drag, and Pitching Moment of an Airplane Employing a Thin, Unswept Wing
- Longitudinal Stability Characteristics of the Consolidated Vultee XFY-1 Airplane with Windmilling Propellers as Obtained from Flight of 0.133-Scale Rocket-Propelled Model at Mach Numbers from 0.70 to 1.13
- 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