Liang WANG, Song FU

DOI Number: 10.60853/g5bp-m743

Conference number: HiSST-2024-00280

This paper presents the authors’ advancements in the investigation of flow instabilities encountered during hypersonic flight. It encapsulates several significant findings, as follows: 1) Elucidation of the excitation mechanisms governing the evolution of the three-dimensional boundary layer at the vehicle nose, with particular emphasis on the impact of thermal–chemical nonequilibrium effects. 2) Observation of a notable decay in disturbance growth-rate oscillation downstream of the turning point, where the unstable supersonic mode transitions back to the subsonic regime. 3) Discovery of novel modes of crossflow vortices occurring on the surface of swept wings.

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In Categories: 1.Events, HiSST 2024, Hypersonic Fundamentals and History
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