Modified Shear-Stress Transport Turbulence Model for Supersonic Flows

Abstract

The shear-stress transport turbulence model of Menter was derived to predict an accurate separated flow in the adverse pressure gradient flowfield, but it has sometimes failed to analyze these regions due to the strong shock/boundary-layer interaction. The modification of the shear-stress transport turbulence model adopted the shear strain rate instead of the vorticity as a limitation of the shear stress. The modified shear-stress transport turbulence model was applied to simulate supersonic compression corner flows including strong shock/boundarylayer interactions, and its performance in predicting the wall pressure distribution and the skin-friction coefficient was evaluated. The pressure distributions on the wall surface predicted by the modified shear-stress transport turbulence model showed an agreement with the experimental data in a transonic axisymmetric bump flow with the weak shock/boundary-layer interaction. In the cases of the 20- and 24-deg compression corner flows with strong shock/boundary-layer interactions, the modified shear-stress transport turbulence model yielded a more accurate prediction of the shock location and the wall pressure distribution and it also produced the more reasonable mean velocity profiles and skin-friction coefficient distribution in the redevelopment region as compared to the shear-stress transport turbulence model.