CFD Evaluation of Mach 17 HYPULSE Scramjet Combustor Data
Three-dimensional finite rate chemistry solutions are performed on a single fuel injector configuration. The results are compared with limited experimental data obtained from the HYPULSE expansion tube facility at simulated flight Mach 17 flow conditions. All comparisons, except for wall heat flux, were in excellent agreement. Key findings from this study are useful in interpretation of the experimental measurements.
G. J. Bobskill et al., "CFD Evaluation of Mach 17 HYPULSE Scramjet Combustor Data," AIAA 3rd International Aerospace Planes Conference, American Institute of Aeronautics and Astronautics (AIAA), Jan 1991.
AIAA 3rd International Aerospace Planes Conference
Mechanical and Aerospace Engineering
National Aeronautics and Space Administration
Keywords and Phrases
Combustion Chambers; Computational Fluid Dynamics; Fuel Injection; Heat Flux; Hypersonic Flight; Mach Number; Single Stage to Orbit Vehicles; Supersonic Combustion Ramjet Engines
Article - Conference proceedings
© 1991 American Institute of Aeronautics and Astronautics (AIAA), All rights reserved.
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