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- Effect of wing-tank location on the drag and trim of a swept-wing model as measured in flight at transonic speeds
- Effects of leading-edge radius and maximum thickness-chord ratio on the variation with Mach number of the aerodynamic characteristics of several thin NACA airfoil sections
- Effects of inlet icing on performance of axial-flow turbojet engine in natural icing conditions
- Effect of ram-jet pressure pulsations on supersonic-diffuser performance
- Evaluation of a ducted-fan power plant designed for high output and good cruise fuel economy
- Effect of Mach number on over-all performance of single-stage axial-flow compressor designed for high pressure ratio
- Effects of molding conditions on some physical properties of glass-fabric unsaturated-polyester laminates
- Effects of sweep on the maximum-lift characteristics of four aspect-ratio-4 wings at transonic speeds
- Experimental damping in pitch of 45 degree triangular wings
- Experimental investigation of the effectiveness of various suction-slot arrangements as a means for increasing the maximum lift of the NACA 65(sub 3)-018 airfoil section
- Experimental investigation of supersonic flow with detached shock waves for Mach numbers between 1.8 and 2.9
- Internal film cooling experiments in 4-inch duct with gas temperatures to 2000 degrees F
- Tabulated pressure coefficients and aerodynamic characteristics measured on the wing of the Bell X-1 airplane in pull-ups at Mach numbers from 0.53 to 0.99
- Study of flow conditions and deflection angle at exit of two-dimensional cascade of turbine rotor blades at critical and supercritical pressure ratios
- Study of compressor systems for a gas-generator engine
- 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