Research on Shock-Boundary Layer Interaction in Hypersonic Inlets
TAN Wei-wei;TIAN Zeng-dong;LIANG Yi-hua;Xi'an Aeronautics Computing Technique Research Institute,AVIC;
This paper focus on the capability of turbulence model to capture shock- boundary layer interaction phenomenon using hybrid grid based CFD solver. While doing this,we choose two test cases,which are compression corner with corner angle 24° and DLR-GK01 two dimensional hypersonic inlets,to evaluate different turbulence model by comparing the simulated flow structure,pressure and friction coefficient. The solutions show that compared to Menter SST turbulence model,SA and Kok's TNT turbulence model are more suitable for simulating those flows with shock- boundary layer interaction phenomenon.