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Hypersonic stagnation point injection experiments are performed in a Mach 6 quiet flow and Mach 5.8 noisy flow free stream. We show how the dominant modes in the flow evolve as a function of the thrust coefficient.
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This page is a summary of: Flow Interaction Dynamics of Stagnation Point Injection in Mach 6 Quiet Flow, Journal of Spacecraft and Rockets, August 2025, American Institute of Aeronautics and Astronautics (AIAA),
DOI: 10.2514/1.a36333.
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