Assessment of CFD Modeling Capability for Hypersonic Shock Wave Boundary Layer Interactions.

摘要

The report assesses the capability of Computational Fluid Dynamics to predict the aerothermodynamic loads on simplified geometries in hypersonic flight. The specific configurations are the double cone and hollow cylinder flare. Experiments conducted at the Calspan University of Buffalo Research Center (CUBRC) at Mach 10.9 to 13.2 and stagnation enthalpies from 5 MJ/kg to 22 MJ/kg. Simulations were performed using the laminar compressible Niavier-Stokes equations and both perfect gas and Park I thermochemistry models. The Park I model demonstrated reliable results for peak heat transfer at all conditions; however, the predictions using Park I for peak pressure and separation length were unreliable.