CFD Evaluation of Mach 17 HYPULSE Scramjet Combustor Data
Abstract
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.
Recommended Citation
G. J. Bobskill et al., "CFD Evaluation of Mach 17 HYPULSE Scramjet Combustor Data," Proceedings of the AIAA 3rd International Aerospace Planes Conference (1991, Orlando, FL), American Institute of Aeronautics and Astronautics (AIAA), Dec 1991.
Meeting Name
3rd International Aerospace Planes Conference, AIAA ARC (1991: Dec. 3-5, Orlando, FL)
Department(s)
Mechanical and Aerospace Engineering
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
Document Type
Article - Conference proceedings
Document Version
Citation
File Type
text
Language(s)
English
Rights
© 1991 American Institute of Aeronautics and Astronautics (AIAA), All rights reserved.
Publication Date
05 Dec 1991
