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Preliminary investigation of a fin-actuated jet-vane control system for stabilization of rocket-powered models

The preparation, physical properties, and heats of combustion of four alkylsilanes

Large-Scale Flight Measurements of Zero-Lift Drag at Mach Numbers from 0.90 to 1.95 of an Arrow Wing in Combination with a Small Body

Langley 9-inch supersonic tunnel tests of several modifications of a supersonic missile having tandem cruciform lifting surfaces : three-component data results of models having ratios of wing span to tail span equal to 1

Langley 9-inch supersonic tunnel tests of several modifications of a supersonic missile having tandem cruciform lifting surfaces : three-component data results of models having ratios of wing span to tail span equal to and less than 1 and some static

Large-scale flight measurements of zero-lift drag at Mach numbers from 0.8 to 1.6 of a wing-body combination having an unswept 4.5 percent thick wing with modified hexagonal sections

Load-Range Performance of Turbine-Propeller Engine in Transonic Speed Range and Comparison with Load-Range Performance of Turbojet Engine

Lift and drag coefficients for the Bell X-1 airplane (8-percent-thick wing) in power-off transonic flight

Longitudinal frequency-response characteristics of a 35 degree swept-wing airplane as determined from flight measurements, including a method for the evaluation of transfer functions

Longitudinal-control effectiveness and downwash characteristics at a Mach number of 1.24 of a 1/30-scale semispan model of the Bell X-5 airplane as determined by the NACA wing-flow method

Low-speed characteristics of a wing having 63 degrees sweepback and uniform camber

Low-speed investigation of a 0.16 scale model of the X-3 airplane : lateral and directional characteristics

Measurements of downwash and sidewash behind cruciform triangular wings at Mach number 1.4

Measurement of distortion in second experimental control rod with temperature patterns simulating shim rod out and shim rod 50 percent inserted for Argonne Naval Reactor / A. F. Lietzke and T. F. Nagey

Flame velocities of four alkylsilanes

Effect of spark repetition rate on the ignition limits of a single tubular combustor

Heat capacity lag in gases

Notes on low-lift buffeting and wing dropping at Mach numbers near 1

Determination of ram-jet combustion-chamber temperatures by means of total-pressure surveys

Criterions for prediction and control of ram-jet flow pulsations

The effect of mass distribution on the low-speed dynamic lateral stability and control characteristics of a model with a 60 degree triangular wing

An analytical investigation using aerodynamic limitations of several designs of high stage pressure ratio multistage compressors

Analytical investigation of ram-jet-engine performance in flight Mach number range from 3 to 7

An investigation of a supersonic aircraft configuration having a tapered wing with circular-arc section and 40 degree sweepback: a pressure-distribution study of the aerodynamic characteristics of the wing at Mach number 1.40

Calculated effects of turbine rotor-blade cooling-air flow, altitude, and compressor bleed point on performance of a turbojet engine

Ceramic coatings for prevention of carbon absorption in four heat-resistant alloys

Combustion performance evaluation of magnesium-hydrocarbon slurry blends in a simulated tail-pipe burner

Combustion properties of aluminum as ram-jet fuel

Wind-tunnel investigation at Mach numbers from 0.50 to 1.29 of an unswept, tapered wing of aspect ratio 2.67 with leading- and trailing-edge flaps - leading-edge flaps deflected

Apparatus for obtaining a supersonic flow of very short duration and some drag measurements obtained with its use

Aerodynamic characteristics of wings designed for structural improvement

Analysis of longitudinal stability and trim of the Bell X-1 airplane at a lift coefficient of 0.3 to Mach numbers near 1.05

Low-speed longitudinal and wake air-flow characteristics at a Reynolds number of 5.5 x 10(exp 6) of a circular-arc 52 degrees sweptback wing with a fuselage and a horizontal tail at various vertical positions

Characteristics of flow over inclined bodies of revolution

Compressor performance characteristics of a python turbine-propeller engine investigated in altitude wind tunnel

Analysis of experimental sea-level transient data and analog method of obtaining altitude response for turbine-propeller engine with relay-type speed control

The effects of Mach number and Reynolds number on the aerodynamic characteristics of several 12-percent-thick wings having 35 degrees of sweepback and various amounts of camber

Effects of humidity during fabrication on some physical properties of glass-fabric unsaturated-polyester laminates

Evaluation of centrifugal compressor performance with water injection

The effects of various parameters including Mach number on propeller blade flutter with emphasis on stall flutter

Experimental investigation of oil film pressure distribution for misaligned plain bearings

Estimated deceleration of airplane nose section jettisoned at various altitudes and airspeeds

Experimental and theoretical study of the effects of body size on the aerodynamic characteristics of an aspect ratio 3.0 wing-body combination

Experimental investigation of effects of design changes on performance of large-capacity centrifugal compressors

Aerodynamic characteristics at transonic speeds of a 69 degree delta wing with a triangular plan-form control having a skewed hinge axis and an overhang balance : transonic-bump method

Aerodynamic characteristics including pressure distribution of a fuselage and three combinations of the fuselage with swept-back wings at high subsonic speeds

Ignition-energy requirements in a single tubular combustor

Tabulated pressure coefficients and aerodynamic characteristics measured on the wing of the Bell X-1 airplane in an unaccelerated stall and in pull-ups at Mach numbers of 0.74, 0.75, 0.94, and 0.97

Tabulated pressure coefficients and aerodynamic characteristics measured on the wing of the Bell X-1 airplane in an unaccelerated low-speed stall, in push-overs at Mach numbers of 0.83 and 0.99, and in a pull-up at a Mach number of 1.16

Simplified method for calculation of compressible laminar boundary with arbitrary free-stream pressure gradient


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