Hugo LEMARQUAND, Mathieu LUGRIN, Cédric CONTENT, Clément CAILLAUD, Sébastien ESQUIEU, Denis SIPP

DOI Number: N/A

Conference number: HiSST-2025-073

Base-flow computations, resolvent, and sensitivity analyses are performed for a hypersonic wind tunnel nozzle at Mach 6. This research precisely identifies, through resolvent analysis, the locations and mechanisms governing the development of the Görtler instability, as well as the first and second Mack modes, within a hypersonic wind tunnel nozzle. Additionally, sensitivity analysis of the resolvent optimal gain provides a pathway to mitigate instability growth, and consequently delay the transition, through wall temperature variation. This methodology can be extended to other forms of control, such as nozzle wall displacement and other key control parameters. Using the sensitivity results, an optimal profile is also designed to simultaneously control several unstable modes. These findings contribute to the advancement of quiet wind tunnels and ground testing facilities for hypersonic flows.

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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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