Computational Simulation of Supersonic Flow Using Reynolds Stress Model

The case of a supersonic turbulent flows with Mach number 2.5 and Reynolds number 1.23×10⁶ based on the diameter of after body, around a body with incidence angles of 14° was studied. The nose length was 3 times the diameter with a third degree polynomial variation, and total length of the body was 13 diameters. Reynolds Averaged Navier-Stokes Equation was solved using central differencing scheme. The Reynolds Stress Model was used to account for the effect of turbulence on the flow field. The experimental data consist of surface pressure measurement at six axial locations. The pressure distributions were compared with the experimental data and the computer simulation results using Baldwin-Lumax and k-ε models. RSM results were found to show good agreement with the experimental data, while the Baldwin-Lumax model predictions deviated from the experimental data at the leeward on the after body because of a large cross-flow separation. The cross-sectional Mach number contours were also presented. It was shown that in addition to the outer shock, a cross-flow shock wave was also present in the flow region.