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In hypersonic flight vehicle designs, intense surface heating and flow unsteadiness are necessary design considerations. To examine these properties, we perform simulations on a generic missile-like body at hypersonic wind tunnel conditions.
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This page is a summary of: Shock-Wave/Boundary-Layer Interaction in Hypersonic Flow over a Missile Configuration, Journal of Spacecraft and Rockets, July 2025, American Institute of Aeronautics and Astronautics (AIAA),
DOI: 10.2514/1.a36312.
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