Abstract

Introduction S UBSCALE model scramjet engines have been tested at Japan Aerospace Exploration Agency—Kakuda Space Propulsion Center (formerly National Aerospace Laboratory—Kakuda Space Propulsion Laboratory).1 The models consisted of a sidecompression-type inlet, a constant (minimum) cross-sectional area isolator with steps at its exit, a constant cross-sectional area combustor with fuel injectors, a diverging combustor, and an internal nozzle. In the tests, occurrence of combustor-inlet interaction2 resulted in a limit to the fuel flow rate and the engine thrust. To mitigate this interaction, a staged combustor, which had firststage fuel injectors on a strut in the minimum cross-sectional area

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