Abstract
Rectangular-to-Elliptical Shape Transition (REST) scramjet engines show promise as an access-to-space technology, due to its desirable on- and off-design performance. However, a Mach 12 REST engine will require signicant improvements to its combustion efficiency to be useful as a part of a hybrid launch system. Fuel injection must therefore be tai- lored to the internal flow of the engine; flow which has been virtually unexamined until now. Simulation of the flow through a Mach 12 REST engine was performed, leading to a characterization of a complex three-dimensional shock structure, which in turn drives the generation of swept separated flow regions in the inlet and combustor. With much of the air flowing along the cowl side of the engine, injection in this region near shock or vortical structures may lead to great increases in engine combustion efficiency.
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