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- Summary report of results obtained during demonstration tests of the Northrop X-4 airplanes
- An 8-foot axisymmetrical fixed nozzle for subsonic Mach numbers up to 0.99 and for a supersonic Mach number of 1.2
- The effect of accelerating a hypothetical aircraft through the transonic range with controls fixed
- Effect of air distribution on radial temperature distribution in one-sixth sector of annular turbojet combustor
- Investigation of the pressure-ratio requirements of the Langley 11-inch hypersonic tunnel with a variable-geometry diffuser
- Lift and pitching-moment interference between a pointed cylindrical body and triangular wings of various aspect ratios at Mach numbers of 1.50 and 2.02
- Free-flight performance of 16-inch-diameter supersonic ram-jet units III : four units designed for combustion-chamber-inlet Mach number of 0.245 at free-stream Mach number of 1.8 (Units D-1, D-2, D-3, and D-4)
- 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 with a wing of 45 degrees sweepback, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfo
- Turbojet-engine evaluation of AISI 321 and AISI 347 stainless steels as nozzle-blade materials
- Tank investigation of the Grumman JRF-5 airplane fitted with hydro-skis suitable for operation on water, snow, and ice
- Altitude performance and operational characteristics of 29-inch-diameter tail-pipe burner with several fuel systems and fuel-cooled stage-type flame holders on J35-A-5 turbojet engine
- Altitude performance characteristics of tail-pipe burner with converging conical burner section on J47 turbojet engine
- Altitude investigation of performance of turbine-propeller engine and its components
- Altitude performance characteristics of turbojet-engine tail-pipe burner with variable-area exhaust nozzle using several fuel systems and flame holders
- A theoretical investigation of the influence of auxiliary damping in pitch on the dynamic characteristics of a proportionally controlled supersonic canard missile configuration
- Wing-tunnel investigation at Mach numbers from 0.50 to 1.29 of an all-movable triangular wing of aspect ratio 4 alone and with a body
- Altitude-wind-tunnel investigation of combustion-chamber performance on J47 turbojet engine
- Altitude-wind-tunnel investigation of operational characteristics of J47 turbojet engine
- A theoretical investigation of the dynamic lateral oscillatory stability of an airplane having a 60 degree triangular wing
- Low-speed lateral stability and aileron-effectiveness characteristics at a Reynolds number of 3.5 x 10(exp 6) of a wing with leading-edge sweepback decreasing from 45 degrees at the root to 20 degrees at the tip
- The path and motion of scale models of jettisonable nose sections at supersonic speeds as determined from an investigation in the Langley free-flight apparatus
- Model flight investigation of a nonlifting winged tow target
- Stability characteristics at low speed of a 1/4-scale Bell X-5 airplane model with various modifications to the basic model configurations
- Stability and control characteristics of a 1/4-scale Bell X-5 airplane model in the landing configuration
- Preliminary investigation of porous walls as a means of reducing tunnel boundary effects at low-supersonic Mach numbers
- Preliminary investigation of heat transfer to water flowing in an electrically heated Inconel tube
- Pressure measurements at supersonic speeds on a section of a rectangular wing having an NACA 65-009 profile
- Stability and control characteristics at low speed of a 1/4-scale Bell X-5 airplane model: Longitudinal stability and control
- An analysis of the forces and pressure distribution on a wing with the leading edge swept back 37.25 degrees
- Elevator-stabilizer effectiveness and trim of the X-1 airplane to a Mach number of 1.06
- Effect of inlet temperature and humidity on thrust augmentation of turbojet engine by compressor-inlet injection
- Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : effectiveness of an elevon as a longitudinal control and the effects of camber and twist on the maximum lift-drag ratio at supersonic speeds
- Numerical solution of equations for one-dimensional gas flow in rotating coolant passages
- Temperature and pressure distributions in dual parallel jets impinging on the ground from a turbojet engine
- Wing-flow measurements of longitudinal stability and control characteristics of a canard airplane configuration with a 45 degree sweptback wing and a triangular all-movable control surface
- Wing-dropping characteristics of some straight and swept wings at transonic speeds as determined with rocket-powered models
- Wing-flow measurements of longitudinal stability and control characteristics of a supersonic airplane configuration having a 42.8 degree sweptback circular arc wing with aspect ratio 4.0, taper ratio 0.50, and sweptback tail surfaces
- Approximate relative-total-pressure losses of an infinite cascade of supersonic blades with finite leading-edge thickness
- An experimental investigation of a jet-engine nacelle in several positions on a 37.25 degree swept-back wing
- Experimental investigation of a flat plate paddle jet vane operating on a rocket jet
- Low-temperature ignition-delay characteristics of several rocket fuels with mixed acid in modified open-cup-type apparatus
- Investigation of centrifugal compressor operated as a centripetal refrigeration turbine
- Cooling of ram jets and tail-pipe burners : analytical method for determining temperatures of combustion chamber having annular cooling passage
- The effects of compressibility on the pressures on a body of revolution and on the aerodynamic characteristics of a wing-nacelle combination consisting of the body of revolution mounted on a swept-back wing
- A comparison of the aerodynamic characteristics at transonic speeds of four wing-fuselage configurations as determined from different test techniques
- The effect of aspect ratio on the subsonic aerodynamic characteristics of wings with NACA 65(sub 1)-210 sections
- Effect of blade-root fit and lubrication on vibration characteristics of ball-root-type axial-flow-compressor blades
- A description of the design of highly swept propeller blades
- Effect of compressor-outlet bleedoff on turbojet-engine performance
- Application of blade cooling to gas turbines