Hypersonic engine component experiments in a high heat flux supersonic flow environment

Herbert Joe Gladden; Matthew E. Melis

doi:10.1117/12.163822

12 November 1993 Hypersonic engine component experiments in a high heat flux supersonic flow environment

Herbert Joe Gladden, Matthew E. Melis

Proceedings Volume 1997, High Heat Flux Engineering II; (1993) https://doi.org/10.1117/12.163822
Event: SPIE's 1993 International Symposium on Optics, Imaging, and Instrumentation, 1993, San Diego, CA, United States

Abstract

The major concern in advancing the state-of-the-art technologies for hypersonic vehicles is the development of an aeropropulsion system capable of withstanding the sustained high thermal loads expected during hypersonic flight. Even though progress has been made in the computational understanding of fluid dynamics and the physics/chemistry of high speed flight, there is also a need for experimental facilities capable of providing a high heat flux environment for testing component concepts and verifying/calibrating these analyses. A hydrogen/oxygen rocket engine heat source has been developed at the NASA Lewis Research Center that is capable of providing heat fluxes up to 450 W/cm² on flat surfaces and up to 5,000 W/cm² at the leading edge stagnation point of a strut in a supersonic flow stream. Gas temperatures up to 3050 K can also be attained. Two recent experimental programs conducted in this facility are discussed.

Citation Download Citation

Herbert Joe Gladden and Matthew E. Melis "Hypersonic engine component experiments in a high heat flux supersonic flow environment", Proc. SPIE 1997, High Heat Flux Engineering II, (12 November 1993); https://doi.org/10.1117/12.163822

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