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- 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
- A correlation by means of transonic similarity rules of the experimentally determined characteristics of 18 cambered wings of rectangular plan form
- Design procedure and limited test results for a high solidity, 12-inch transonic impeller with axial discharge
- A design and performance study of the nuclear direct-air-cycle supersonic airplane, including the effects of operating temperatures and fuel plate material and thickness
- Design and test of mixed-flow impellers 3: design and experimental results for impeller model MFI-2A and comparison with impeller model MFI-1A
- Design considerations for mixed-flow centrifugal compressors with high weight-flow rates per unit frontal area
- Effect of particle size and stabilizing additives on the combustion properties of magnesium slurry
- Analytical studies of the response to longitudinal control of three airplane configurations in landing approaches
- An analytical study of sideslip angles and vertical-tail loads in rolling pullouts as affected by some characteristics of modern high-speed airplane configurations
- An analytical study of the comparative performance of six air-induction systems for turbojet-powered airplanes designed to operate at Mach numbers up to 2.0
- Air-flow characteristics of brazed and rolled wire filter cloth for transpiration-cooled afterburners
- Buffeting of a vertical tail on an inclined body at supersonic Mach numbers
- Burning rates of single fuel drops and their application to turbojet combustion process
- A cascade-general-momentum theory of operation of a supersonic propeller annulus
- Analysis of part-speed operation for high-pressure-ratio multistage axial-flow compressors
- Static lateral stability characteristics of an airplane model having a 47.7 degree sweptback wing of aspect ratio 6 and the contribution of various model components at a Reynolds number of 4.45 x 10(exp 6)