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QUEENSLAND UNIV BRISBANE (AUSTRALIA) CENTRE FOR HYPERSONICS
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Scramjet operation in the lower hypersonic regime between Mach 4 and 8 is characterized by what is called dual-mode combustion. In this situation disturbances generated by heat-release in the combustor can propagate upstream of fuel injection to affect the operation of the inlet. The method use to alleviate this problem is installation of a short duct between the inlet and the combustor known as an isolator. This article describes the flow phenomenon that exits in the isolator in these situations and presents some of the current methodologies and analysis techniques for scramjet isolator design.
APPROVED FOR PUBLIC RELEASE