Abstract
Computational fluid dynamic (CFD) analyses of the University of Michigan (UM) Shock Boundary-Layer Interaction (SBLI) experiments were performed as an extension of the CFD SBLI Workshop held at the 48th AIAA Aerospace Sciences Meeting in 2010. In particular, the UM Mach 2.75 Glass Tunnel with a semi-spanning 7.75 degree wedge was analyzed in attempts to explore key physics pertinent to SBLI’s, including thermodynamic and viscous boundary conditions. A fundamental exploration pertaining to the effects of particle image velocimetry (PIV) on post-processing data is also shown. Results showed an improvement in agreement with experimental data with key contributions by adding a laminar zone upstream of the wedge (the flow is considered transitional downstream of the nozzle throat) and the necessity of mimicking PIV particle lag for comparisons. All CFD analyses utilized the OVERFLOW solver.
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