New Design Method of a Supersonic Steam Injection Nozzle and Its Numerical Simulation Verification. [PDF]
ACS Omega, 2023 Wang Q, Pang Z, Tian C, Chen J.
europepmc +1 more source
QCGAT mixer compound exhaust system design and static big model test report [PDF]
A mixer exhaust system was designed to meet the proposed performance and exhaust jet noise goals for the AiResearch QCGAT engine. Some 0.35 scale models of the various nozzles were fabricated and aerodynamically and acoustically tested.
Blackmore, W. L., Thompson, C. E.
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The Applications Technology Satellite apogee rocket motor - A summary report [PDF]
Design, testing, and development of solid propellant rocket engine for orbital transfer of Applications Technology ...
Anderson, R. G.
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Improvement of a large-amplitude sinusoidal pressure generator for dynamic calibration of pressure transducers [PDF]
Results of research on the improvement of a sinusoidal pressure generator are presented. The generator is an inlet-area-modulated, gas-flow-through device (siren type) which was developed to dynamically calibrate pressure transducers and pressure probes.
Robinson, R. E.
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An inventory of aeronautical ground research facilities. Volume 1: Wind tunnels [PDF]
A survey of wind tunnel research facilities in the United States is presented. The inventory includes all subsonic, transonic, and hypersonic wind tunnels operated by governmental and private organizations.
Brown, K. R. +3 more
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Multiple steady states for characteristic initial value problems [PDF]
The time dependent, isentropic, quasi-one-dimensional equations of gas dynamics and other model equations are considered under the constraint of characteristic boundary conditions.
Abarbanel, S. +2 more
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A study of the durability of beryllium rocket engines [PDF]
An experimental test program was performed to demonstrate the durability of a beryllium INTEREGEN rocket engine when operating under conditions simulating the space shuttle reaction control system.
French, G. C., Paster, R. D.
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Modification of NASA Langley 8 foot high temperature tunnel to provide a unique national research facility for hypersonic air-breathing propulsion systems [PDF]
A planned modification of the NASA Langley 8-Foot High Temperature Tunnel to make it a unique national research facility for hypersonic air-breathing propulsion systems is described, and some of the ongoing supporting research for that modification is ...
Kelly, H. N., Wieting, A. R.
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Sounding rocket reliability reassessment [PDF]
Sounding rocket reliability - failure ...
Hisler, A.
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Effects of Cavity on the Performance of Dual Throat Nozzle During the Thrust-Vectoring Starting Transient Process. [PDF]
J Eng Gas Turbine Power, 2014 Gu R, Xu J.
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