Selwyn VAN DER LAAN, Mathieu LUGRIN, Clément CAILLAUD, Cédric CONTENT, Denis SIPP

DOI Number: N/A

Conference number: HiSST-2025-082

A numerical study analyzes boundary layer stability over a Cone-Cylinder-Flare (CCF) geometry at Mach 6 and Reynolds number Re = 4.62× 106 [m−1], focusing on the impact of wall-to-recovery temperature similarity on hypersonic transition. Three cases are compared: typical cold-wall flight, standard wind tunnel conditions, and a third case with enhanced wall cooling to match flight similarity parameters. Global stability and resolvent analyses reveal that wall cooling and higher stagnation temperatures significantly destabilize global modes. While both first and second Mack modes are active in tunnel tests, only the second mode dominates in flight. The third case, with temperature similarity, successfully
replicates flight transition mechanisms despite lower stagnation temperatures. These results highlight the crucial role of wall-to-recovery temperature in accurately modeling hypersonic transition and the limitations of conventional ground testing.

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In Categories: 1.Events, 1.HiSST 2025, High-Speed Aerodynamics and Aerothermodynamics with application to hypersonic regimes
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