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- Effect of spark repetition rate on the ignition limits of a single tubular combustor
- Heat capacity lag in gases
- Notes on low-lift buffeting and wing dropping at Mach numbers near 1
- Determination of ram-jet combustion-chamber temperatures by means of total-pressure surveys
- Criterions for prediction and control of ram-jet flow pulsations
- The effect of mass distribution on the low-speed dynamic lateral stability and control characteristics of a model with a 60 degree triangular wing
- An analytical investigation using aerodynamic limitations of several designs of high stage pressure ratio multistage compressors
- Analytical investigation of ram-jet-engine performance in flight Mach number range from 3 to 7
- An investigation of a supersonic aircraft configuration having a tapered wing with circular-arc section and 40 degree sweepback: a pressure-distribution study of the aerodynamic characteristics of the wing at Mach number 1.40
- Aerodynamic characteristics of wings designed for structural improvement
- Calculated effects of turbine rotor-blade cooling-air flow, altitude, and compressor bleed point on performance of a turbojet engine
- Ceramic coatings for prevention of carbon absorption in four heat-resistant alloys
- Combustion performance evaluation of magnesium-hydrocarbon slurry blends in a simulated tail-pipe burner
- Combustion properties of aluminum as ram-jet fuel
- Wind-tunnel investigation at Mach numbers from 0.50 to 1.29 of an unswept, tapered wing of aspect ratio 2.67 with leading- and trailing-edge flaps - leading-edge flaps deflected
- Apparatus for obtaining a supersonic flow of very short duration and some drag measurements obtained with its use
- Analysis of longitudinal stability and trim of the Bell X-1 airplane at a lift coefficient of 0.3 to Mach numbers near 1.05
- Low-speed longitudinal and wake air-flow characteristics at a Reynolds number of 5.5 x 10(exp 6) of a circular-arc 52 degrees sweptback wing with a fuselage and a horizontal tail at various vertical positions
- Characteristics of flow over inclined bodies of revolution
- Compressor performance characteristics of a python turbine-propeller engine investigated in altitude wind tunnel
- Analysis of experimental sea-level transient data and analog method of obtaining altitude response for turbine-propeller engine with relay-type speed control
- The effects of Mach number and Reynolds number on the aerodynamic characteristics of several 12-percent-thick wings having 35 degrees of sweepback and various amounts of camber
- Effects of humidity during fabrication on some physical properties of glass-fabric unsaturated-polyester laminates
- Evaluation of centrifugal compressor performance with water injection
- The effects of various parameters including Mach number on propeller blade flutter with emphasis on stall flutter
- Experimental investigation of oil film pressure distribution for misaligned plain bearings
- Estimated deceleration of airplane nose section jettisoned at various altitudes and airspeeds
- Experimental and theoretical study of the effects of body size on the aerodynamic characteristics of an aspect ratio 3.0 wing-body combination
- Experimental investigation of effects of design changes on performance of large-capacity centrifugal compressors
- Aerodynamic characteristics at transonic speeds of a 69 degree delta wing with a triangular plan-form control having a skewed hinge axis and an overhang balance : transonic-bump method
- Aerodynamic characteristics including pressure distribution of a fuselage and three combinations of the fuselage with swept-back wings at high subsonic speeds
- Ignition-energy requirements in a single tubular combustor
- Tabulated pressure coefficients and aerodynamic characteristics measured on the wing of the Bell X-1 airplane in an unaccelerated stall and in pull-ups at Mach numbers of 0.74, 0.75, 0.94, and 0.97
- Tabulated pressure coefficients and aerodynamic characteristics measured on the wing of the Bell X-1 airplane in an unaccelerated low-speed stall, in push-overs at Mach numbers of 0.83 and 0.99, and in a pull-up at a Mach number of 1.16
- Simplified method for calculation of compressible laminar boundary with arbitrary free-stream pressure gradient
- Some properties of beryllium oxide and beryllium oxide - columbium ceramals
- Some low-speed characteristics of an air-induction system having scoop-type inlets with provisions for boundary-layer control
- Status of combustion research on high-energy fuels for ram jets
- Sound from a two-blade propeller at supersonic tip speeds
- Static longitudinal stability and dynamic characteristics at high angles of attack and at low Reynolds numbers of a model of the X-3 supersonic research airplane
- The properties of three cast polyester resins of Sierracin 212, 212A, and 250A
- A study of slip formation in polycrystalline aluminum
- An experimental study at moderate and high subsonic speeds of the flow over wings with 30 degrees and 45 degrees of sweepforward in conjunction with a fuselage
- Dynamic stability and control characteristics of a vertically rising airplane model in hovering flight
- An experimental study at moderate and high subsonic speeds of the flow over wings with 30 degrees and 45 degrees of sweepback in conjunction with a fuselage
- Investigation in the Ames 12-foot pressure wind tunnel of a model horizontal tail of aspect ratio 3 and taper ratio 0.5 having the quarter-chord line swept back 45 degrees
- Investigation of altitude starting and acceleration characteristics of J47 turbojet engine
- Subsonic Mach and Reynolds number effects on the surface pressures, gap flow, pressure recovery, and drag of a nonrotating NACA 1-series E-type cowling at an angle of attack of 0 degrees
- A transonic-wing investigation in the Langley 8-foot high-speed tunnel at high subsonic Mach numbers and at a Mach number of 1.2 : wing-fuselage configuration having a wing of 60 degree sweepback, aspect-ratio 4, taper ratio 0.6, and NACA 65A006 airf
- A transonic-wing investigation in the Langley 8-foot high-speed tunnel at high subsonic Mach numbers and at a Mach number of 1.2. : wing-fuselage configuration having a wing of 0 degrees sweepback, aspect ratio 4.0,taper ratio 0.6, and NACA 65A006 ai