Abstract
Three different sub-grid scale large eddy simulations (LES) were assessed for shock wave turbulent boundary layer interaction (STBLI) of hypersonic flow over hollow cylinder flare with Ansys Fluent. The incoming flow is at Mach 6 with Re=〖5.33×10〗^7 and is modeled as an ideal gas. The Smagorinsky-Lilly model, wall-adapting local eddy-viscosity (WALE), and wall-modeled LES (WMLES) were evaluated, with the mesh containing enough cells in the STBLI region to resolve at least 80% of the energy eddies. All the CFD simulations were compared with experimental data of a large hollow cylinder flare from CUBRC data. Data of Surface pressure and heat transfer from the LES models are compared and presented.
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