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- Use of flame-immersed blades to improve combustion limits and efficiency of a 5-inch diameter connected-pipe, ram-jet combustor
- Subsonic static longitudinal stability and control characteristics of a wing-body combination having a pointed wing of aspect ratio 2 with constant-percent-chord trailing-edge elevons
- A summary of data on the division of loads for various wing-fuselage combinations
- A transonic wind-tunnel investigation of the effects of body indentation, as specified by the transonic drag-rise rule, on the aerodynamic characteristics and flow phenomena of a 45 degree sweptback-wing-body combination
- Turbine design considerations for turbine-propeller engine operating over a range of flight conditions
- Turbojet-engine thrust augmentation at altitude by combined ammonia injection into the compressor inlet and afterburning
- A transonic wind-tunnel investigation of the longitudinal stability and control characteristics of a 0.09-scale model of the Bell X-5 research airplane and comparison with flight
- Altitude investigation of XJ34-WE-32 engine performance without electronic control
- Altitude operational characteristics of prototype J40-WE-8 turbojet engine
- Altitude evaluation of several afterburner design variables on a J47-GE-17 turbojet engine
- Wind-tunnel investigation of the aerodynamic characteristics in pitch of wing-fuselage combinations at high subsonic speeds: taper-ratio series
- Wind-tunnel investigation of stall control by suction through a porous leading edge on a 37 degree sweptback wing of aspect ratio 6 at Reynolds numbers from 2.50 x 10(exp 6) to 8.10 x 10(exp 6)
- Altitude performance investigation of a high-temperature afterburner
- Altitude performance investigation of two single-annular type combustors and the prototype J40-WE-8 turbojet engine combustor with various combustor-inlet air pressure profiles
- Altitude performance of a 20-inch-diameter ram-jet engine investigated in a free jet facility at Mach number 3.0
- Altitude performance characteristics of the J47-25 turbojet engine: data presentation
- Aerodynamic characteristics at Mach number 4.04 of a rectangular wing of aspect ratio 1.33 having a 6-percent-thick circular-arc profile and a 30-percent-chord full-span trailing-edge flap
- Adhesive and protective characteristics of ceramic coating A-417 and its effect on engine life of forged Refractaloy-26 (AMS 5760) and cast stellite 21 (AMS 5385) turbine blades
- A theoretical study of the effect of control-deflection and control-rate limitations on the normal acceleration and roll response of a supersonic interceptor
- Transonic aerodynamic characteristics of an NACA 64A006 airfoil section with a 15-percent-chord leading-edge flap.
- Theoretical study of the tunnel-boundary lift interference due to slotted walls in the presence of the trailing-vortex system of a lifting model
- Low-speed, large-scale investigation of aerodynamic characteristics of a semispan 49 degree sweptback wing with a Fowler flap in combination with a plain flap, slats, and fences
- Low-speed lateral control characteristics of an unswept wing with hexagonal airfoil sections and aspect ratio 4.0 at a Reynolds number of 6.2 x 10(exp 6)
- Low-speed wind-tunnel investigation of a thin 60 degree delta wing with double slotted, single slotted, plain, and split flaps
- Low-speed static stability and control characteristics of a 1/4-scale model of the Bell X-1 airplane equipped with a 4-percent-thick, aspect-ratio-4, unswept wing
- Investigation of the use of a stick force proportional to pitching acceleration for normal-acceleration warning
- Minimum spark-ignition energies of 12 pure fuels at atmospheric and reduced pressure
- Prediction of flame velocities of hydrocarbon flames
- The Sodium Hydroxide Reactor : Effect of Reactor Variables on Criticality and Fuel-Element Temperature Requirements for Subsonic and Supersonic Aircraft Nuclear Propulsion
- Some approximate methods for estimating the effects of aeroelastic bending of rocket-propelled model-booster combinations
- Smoke studies of secondary flows in bends, tandem cascades, and high-turning configurations
- Model ditching investigations of three airplanes equipped with hydro-skis
- Performance comparison at supersonic speeds of inlets spilling excess flow by means of bow shock, conical shock, or bypass
- Performance comparison of three canard-type ram-jet missile configurations at Mach numbers from 1.5 to 2.0
- Preliminary investigation of plate-type molybdenum disilicide fuel elements for an air-cycle nuclear reactor
- Stability of bodies of revolution having fineness ratios smaller than 1.0 and having rounded fronts and blunt bases
- Air-flow and thrust characteristics of several cylindrical cooling-air ejectors with a primary to secondary temperature ratio of 1.0
- Influence of end plates on lift and flow field of a canard-type control surface at a Mach number of 2.00
- Hinge-moment characteristics for several tip controls on a 60 degree sweptback delta wing at Mach number 1.61
- Effect of inlet oxygen concentration on combustion efficiency of J33 single combustor operating with gaseous propane
- Force and pressure recovery characteristics at supersonic speeds of a conical spike inlet with bypasses discharging in an axial direction
- Force and pressure recovery characteristics at supersonic speeds of a conical spike inlet with a bypass discharging from the top or bottom of the diffuser in an axial direction
- Forced-convection heat-transfer characteristics of molten sodium hydroxide
- Altitude wind tunnel investigation of the prototype J40-WE-8 turbojet engine without afterburner
- Considerations in the adaptation of low-cost fuels to gas-turbine-powered commercial aircraft
- Aerodynamics of slender bodies at Mach number of 3.12 and Reynolds numbers from 2 x 10(exp 6) to 15 x 10(exp 6) III : boundary layer and force measurements on a slender cone-cylinder body of revolution
- Acceleration of high-pressure-ratio single-spool turbojet engine as determined from component performance characteristics : effect of compressor interstage air bleed
- Experimental investigation of an axial-flow supersonic compressor having rounded leading-edge blades with an 8-percent mean thickness-chord ratio
- Experimental investigation of an axial-flow compressor inlet stage operating at transonic relative inlet Mach numbers III : blade-row performance of stage with transonic rotor and subsonic stator at corrected tip speeds of 800 and 1000 feet per secon
- Investigation at a Mach number of 1.90 of a diverter-type boundary-layer removal system for a scoop inlet