Numerical Analysis of Wall Properties in Crossing-Shock-Wave/Turbulent-Boundary-Layer Interactions

Abstract

o× 11 o case is thus only performed on the fine grid. For all three cases, the computed static pressure and wall heat transfer coefficient variations along the throat middle line (TML) and three cross-section locations have shown fairly good agreement with the experimental measurements and computational results from other researchers. The near-wall flow topologies have also shown good qualitatively agreement with the experimental visualization. For the 15 o × 15 o case, the computed heat transfer coefficient has exhibited significant decrease around the interaction region, which was not observed in the experiments. Further studies have been focused on this strong interaction case and the turbulent models influences on the static pressure and heat transfer coefficient predictions have been investigated. It was found that the turbulence model has little influence on static pressure distribution, but has significant impact on heat transfer coefficient with the RNG k-�0 model producing violated results and the shear stress transport and eddy viscosity transport models producing results in better agreement with the test data. Due to strong shock-wave boundary layer interactions, flow separation exists and this has been revealed by velocity vectors and skin friction coefficients. It was believed that the decrease of wall heat transfer coefficient is related with flow separation that might alter the near-wall temperature profile. Several temperature profiles have thus been plotted and confirmed this hypothesis.