Peisen LU, Youcheng XI, Song FU

DOI Number: 10.60853/452e-0006

Conference number: HiSST-2024-00179

The expansion corner is a typical kind of structure on swept wings of hypersonic vehicles, which has a great effect on crossflow instabilities. This work aims to investigate the actual effect of the expansion corner on linear instabilities in practical three-dimensional hypersonic flow regimes. Hypersonic swept flows over a designed wing model of real vehicles are studied. The flow is calculated at a free-stream Mach number of 6 with the adiabatic wall condition. The model consists of a blunt cone, after which comes an expansion corner along with a flat plate. The corresponding laminar flow computations with different swept angles have been carried out using in-house shock-fitting procedures in order to ensure the quality of the base flow. Linear stability theory (LST) has been incorporated in investigating the effects of expansion corner on stationary crossflow instabilities. The most unstable mode which dominates the instability behaviour is calculated at interested streamwise locations. Both growth rates curves and neutral curves are calculated to illuminate the instabilities in this regime.

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