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- Investigation of a 10-stage subsonic axial-flow research compressor 3: investigation of rotating stall, blade vibration and surge at low and intermediate compressor speeds
- Investigation of a 10-stage subsonic axial-flow research compressor IV : individual stage performance characteristics
- An investigation of a four-blade single-rotation propeller in combination with an NACA 1-series D-type cowing at Mach numbers up to 0.83
- Investigation of a high-pressure-ratio eight-stage axial-flow research compressor with two transonic inlet stages I : aerodynamic design
- Investigation of a chromium plus aluminum oxide metal-ceramic body for possible gas turbine blade application
- Investigation of a high-pressure-ratio eight-stage axial-flow research compressor with two transonic inlet stages II : preliminary analysis of over-all performance
- Initial flutter tests in the Langley transonic blowdown tunnel and comparison with free-flight flutter results
- An investigation of three NACA 1-series nose inlets at subsonic and transonic speeds
- A flight comparison of a submerged inlet and a scoop inlet at transonic speeds
- Investigation of water-spray cooling of turbine blades in a turbojet engine
- Investigation to determine effects of rectangular vortex generators on the static pressure drop through a 90 degrees circular elbow
- An investigation of some factors affecting the drag of relatively large nonlifting bodies of revolution in a slotted transonic wind tunnel
- Investigation of Spoiler Ailerons with and Without a Gap Behind the Spoiler on a 45 Degree Sweptback Wing-Fuselage Combination at Mach Numbers from 0.60 to 1.03
- Investigation of low-pressure performance of experimental tubular combustors differing in air-entry-hole geometry
- Vapor pressures of concentrated nitric acid solutions in the composition range 83 to 97 percent nitric acid 0 to 6 percent nitrogen dioxide, 0 to 15 percent water, and in the temperature range 20 to 80 C
- Lift and center of pressure of wing-body-tail combinations at subsonic, transonic, and supersonic speeds
- Stability and control characteristics at low speed of a modified 1/10-scale model of the MX-1554A design
- Stability and control characteristics at low speed of a 1/10-scale model of MX-1554A design
- Jet effects on flow over afterbodies in supersonic stream
- Evaluation of effects of random permeability variations on transpiration-cooled surfaces
- Effect of circumferential location on angle of attack performance of twin half-conical scoop-type inlets mounted symmetrically on the RM-10 body of revolution
- An investigation of high-frequency combustion oscillations in liquid-propellant rocket engines
- An experimental investigation of boundary interference on force and moment characteristics of lifting models in the Langley 16- and 8-foot transonic tunnels
- Effect of uneven air-flow distribution to the twin inlets of an axial-flow turbojet engine
- Performance of separation nose inlets at Mach number 5.5
- Orthotoluidine and triethylamine in rocket engine applications
- Tests in the Ames 40- by 80-foot wind tunnel of an airplane configuration with a variable-incidence triangular wing and an all-movable horizontal tail
- Tests in the Ames 40- by 80-foot wind tunnel of an airplane configuration with an aspect ratio 3 triangular wing and an all-movable horizontal tail: Longitudinal and lateral characteristics
- Preliminary comparison of 17- and 75-millimeter-bore cageless cylindrical roller bearings with conventional cylindrical roller bearings at high speeds
- Large-scale flight measurements of zero-lift drag and low-lift longitudinal characteristics of a diamond-wing-body combination at Mach numbers from 0.725 to 1.54
- Preliminary flight measurements of the dynamic longitudinal stability characteristics of the Convair XF-92A delta-wing airplane
- Preliminary investigation of a variable-area auxiliary air-intake system at Mach numbers from 0 to 1.3
- Preliminary experimental investigation of transpiration cooling for an afterburner with a sintered, porous stainless-steel combustion-chamber wall
- Pressure distribution at Mach numbers up to 0.90 on a cambered and twisted wing having 40 degrees of sweepback and an aspect ratio of 10, including the effects of fences
- Langley full-scale-tunnel tests of the Custer Channel Wing airplane
- Lift and Drag Characteristics of the Bell X-5 Research Airplane at 59 Degrees Sweepback for Mach Numbers from 0.60 to 1.03
- The lateral control characteristics of constant-percent-chord trailing-edge elevons on a pointed wing of aspect ratio 2 at Mach numbers up to 0.95
- Loads experienced in flights of two swept-wing research airplanes in the angle-of-attack range of reduced stability
- Low-lift drag and stability data from rocket models of a modified-delta-wing airplane with and without external stores at Mach numbers from 0.8 to 1.36
- Longitudinal flight characteristics of the Bell X-5 research airplane at 59 degree sweepback with modified wing roots
- Longitudinal-control effectiveness and downwash characteristics at transonic speeds of a 1/30-scale semispan model of the Bell X-5 airplane as determined by the NACA wing-flow method
- Measurements of fluctuating pressures on a 1/4-scale model of the X-1 airplane with a 10-percent-thick wing in the Langley 16-foot transonic tunnel
- Measurement and analysis of turbulent flow containing periodic flow fluctuations
- Evaluation of ethyl ether as an ignition aid for turbojet engine fuels
- An experimental investigation of the applicability of the hypersonic similarity law to bodies of revolution
- Effect of engine and control limits on steady-state and transient performance of turbojet engine with variable-area exhaust nozzle
- Effect of drawbar upstream location on air velocity distribution at the inlet face of reactor segment designed by the General Electric Company
- The effect of nacelle combinations and size on the zero-lift drag of a 45 degree sweptback wing and body configuration as determined by free-flight tests at Mach numbers between 0.8 and 1.3
- Effect of flame-holder design on altitude performance of louvered-liner afterburner
- Effect of fuels on combustion efficiency of 5-inch ram-jet-type combustor