Andrew PILKINGTON, Luke J DOHERTY, Chris J HAMBIDGE, Matthew MCGILVRAY, Tristan VANYAI, Vincent WHEATLEY

DOI Number: XXX-YYY-ZZZ

Conference number: HiSST2024-00242

Scramjet engines used as part of a multi-stage space access system must operate efficiently over a wide range of conditions. This paper describes experimental testing undertaken to evaluate the mass capture performance, self starting capability and back pressure limitations of a streamline-traced three dimensional inlet. Experiments were conducted in the University of Oxford High Density Tunnel. Instrumentation included fast-response surface pressure measurements along the inlet, and a novel back pressure/mass capture device suitable for accurate measurement of mass flow rate in short duration testing. Tests were performed at Mach 7 over a range of unit Reynolds numbers to evaluate the inlet.

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In Categories: 1.Events, HiSST 2024, Propulsion Systems and Components
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