Vignesh P, Mohammad Ibrahim SUGRANO

DOI Number: XXX-YYY-ZZZ

Conference number: HiSST2024-00209

Shock Wave Boundary Layer Interaction (SWBLI) is inevitable in the case of supersonic and hypersonic flows. SWBLI is typically encountered in the intake of Scramjet inlet and isolator, vehicle surface geometry changes, control surface deflections, at the junction of body-wing of aircraft, etc. For BFS, the dynamics of the SWBLI region and the associated unsteadiness are available only for supersonic Mach numbers, to the best of our knowledge. This study will involve understanding the flow physics under different Hypersonic Mach numbers of 4 and 6. The free stream conditions used for this study including the free stream Mach number, pressure, and temperature correspond to the S1 Hypersonic facility (Ludwieg tunnel) at Hypersonic Experimental Aerodynamics Laboratory (HEAL) at the Indian Institute of Technology, Kanpur. The SWBLI region over a BFS consists of a boundary layer undergoing rapid expansion, Separation bubble, lip shock-reattachment shock interaction, shock shear layer interaction, etc. The aim is to study and characterize the SWBLI region and associated flow unsteadiness over a BFS configuration in a hypersonic flow. The effect of Reynolds number and step height on flow unsteadiness and its influence on the downstream flow field will also be studied. Work is in progress and the numerical results will be presented.

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In Categories: 1.Events, High-Speed Aerodynamics and Aerothermodynamics, HiSST 2024
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