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Investigation of Effect of Number and Width of Annular Flameholder Gutters on...
Memorandum presenting an investigation of the effect of the number and width of annular flame-holder gutters on afterburner performance in a 26-inch-diameter afterburner test rig. The burner inlet...
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Boundary-Layer Displacement Effects in Air at Mach Numbers of 6.8 and 9.6
"Measurements are presented for pressure gradients induced by a laminar boundary layer on a flat plate in air at a Mach number of 9.6 and for the drag of thin wings at a Mach number of about 6.8 and...
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Effect of Hinge-Line Position on the Oscillating Hinge Moments and Flutter...
Free oscillation test to determine hinge moment of trailing-edge, flap control surface with various hinge-line positions at transonic speed. Results show that oscillating amplitude has a large effect...
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Investigation of an Air-Cooled, Plug-Type, Variable-Area Exhaust Nozzle
Memorandum presenting an experimental investigation of the cooling requirements and internal thrust performance of an air-cooled, plug-type, variable-area exhaust nozzle in a turbojet-engine...
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Attenuation of Tangential-Pressure Oscillations in a Liquid-Oxygen-n-Heptane...
Attenuation of tangent-pressure oscillation in liquid-oxygen-heptane rocket engine combustion chamber using longitudinal fin. Results regarding the engine performance with injector A, effect of fins...
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Experimental Sea-Level Static Investigation of a Short Afterburner
Sea-level static testing of turbojet engine afterburner.
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Empirical Cooling Correlation for an Experimental Afterburner With an Annular...
Memorandum presenting an empirical cooling correlation for an experimental high-performance afterburner. The correlation relates the average combustion-chamber wall temperature at a station near the...
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Total-Pressure-Recovery Characteristics of a Model of the McDonnell XF3H-1...
Report presenting free jet tests of a model of the inlets and forebody of the McDonnell XF3H-1 airplane with the original and two alternate nose shapes. Results regarding the total-pressure recovery...
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An Investigation of Jet Effects on Adjacent Surfaces
"The steady pressure loads as well as the temperature change on adjacent surfaces due to the presence of a propulsive jet at subsonic speeds is shown to be insignificant. Whereas at supersonic speeds...
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Design and Experimental Investigation of a Single-Stage Turbine With a Rotor...
Memorandum presenting a design and experimental investigation of a single-stage supersonic turbine. The turbine was designed for a rotor entering relative Mach number of 2. Results regarding the...
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Aerodynamic Characteristics of Low-aspect-ratio Wings at High Supersonic Mach...
Memorandum presenting some recently obtained data on the aerodynamic characteristics of low-aspect-ratio wings at supersonic Mach number of 4.04 and 6.9 and discusses some new methods of predicting the...
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Investigation of Wingless Missile Configurations with Folding Controls and...
Results regarding a wind-tunnel investigation of wingless missile configurations with cylindrical bodies and conical or hemispherical noses, extensible control surfaces aft of the nose, and tails...
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Influence of Combustion-chamber Length on Afterburner Performance
Memorandum presenting an investigation of the influence of combustion-chamber length on afterburner performance under conditions simulating altitude flight. Results regarding afterburner-inlet...
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Free-Flight Investigation of Aerodynamic Heat Transfer to a Simulated...
"Heat-transfer measurements were made on a simulated glide-rocket shape in free flight at Mach numbers up to 10 and free-stream Reynolds numbers of 2 x 10 based on distance along surface from apex and...
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Heat Transfer Measured in Free Flight on a Slightly Blunted 25 Degree...
Skin temperature and surface pressure of blunted cone-cylinder-flare configuration free flight test vehicle to hypersonic speeds.
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Examination of Recent Lateral-Stability-Derivative Data
"In the present paper attention is directed to the aerodynamic parameters, the so-called stability derivatives, that affect the lateral behavior of airplanes and missiles. The discussion is centered on...
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An Investigation of the Performance of a Semielliptical Scoop Inlet at Mach...
Memorandum presenting an investigation of the performance of a semielliptical scoop inlet with a two-dimensional flow field at the design Mach number of 2.0. The investigation included a study of the...
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Transonic Flutter Investigation of an All-Movable Horizontal Tail for a...
Memorandum presenting a transonic flutter investigation of a model of an all-movable horizontal tail for a fighter airplane. The model had an aspect ratio of 3.3, a taper ratio of 0.42, and 35 degrees...
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Total-Pressure Distortion and Recovery of Supersonic Nose Inlet With Conical...
Memorandum presenting an investigation of ice formation on a full-scale unheated supersonic nose inlet in the icing tunnel to determine its effect on compressor-face total-pressure distortion and...
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Use of Constant Diffuser Mach Number as a Control Parameter for...
Memorandum presenting an analysis to determine the feasibility of using a constant diffuser Mach number to position a translating spike for optimum inlet performance. A control system incorporating...
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