Assessment of CFD Capability for Hypersonic Shock Wave Boundary Layer Interactions, Part Ⅱ

摘要

The goal of this study is to assess CFD capability for prediction of laminar shock wave/ boundary layer interactions at hypersonic velocities. More specifically, the flowfield over a double cone configuration is simulated using both perfect and real gas models. Computations are compared with experimental data obtained from measurements conducted in the LENS XX shock tunnel at CUBRC. Four separate cases of freestream conditions are simulated to examine the numerical methods in a wide range of enthalpies. The results of this investigation can provide factors for design optimization of hypersonic air vehicles.