Study on Scramjet Engine Characteristics Under Mach 8 TO 15 Conditions

Details Study on Scramjet Engine Characteristics Under Mach 8 TO 15 Conditions Study on Scramjet Engine Characteristics Under Mach 8 TO 15 Conditions

Feb 2005

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2005esasp.563..525i&link_type=abstract

Proceedings of the Fifth European Symposium on Aerothermodynamics for Space Vehicles (ESA SP-563). 8-11 November 2004, Cologne,

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Scientific paper

It is known that a Scramjet engine performance is strongly limited due to a significant reduction in net heat release of Fuel/Air combustion at hypervelocity condition. In order to improve the hypervelocity Scramjet performance a Fuel/Air mixing enhancement and an optimization of combustor temperature, which are expected to recover the net heat release, have been studied based on the experiments in a high enthalpy shock tunnel HIEST. Two kind of engines were designed for these purposes and they were tested at Mach 8 to 15 conditions in the HIEST. In the present paper, the improvement of the hypervelocity Scramjet performance is discussed based on the test results of these engines.

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