Title

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.

Meeting Name

AIAA 3rd International Aerospace Planes Conference

Department(s)

Mechanical and Aerospace Engineering

Sponsor(s)

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

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.

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