Numerical investigation of supersonic injection using a Reynolds-Stress turbulence model

The full, three-dimensional Favre-averaged Navier-Stokes equations, coupled with the second-order Zhang et al. (Zhang, H., So, R., Gatski, T., and Speziale, C.,"A Near-Wall Second-Order Closure for Compressible Turbulent Flows," Near-Wall Turbulent Flows, edited by R. So, C. Speziale, and a. Launder, Elsevier, New York, 1993, ppt 209-218) Reynolds-stress turbulence and K-epsilon models, were used to numerically simulate a 25 deg, Mach 1.8 injection into a Mach 3.0 crossflow. Detailed comparisons with experimental data were performed. Analysis of the Reynolds-stress turbulence model simulation results revealed physically consistent and accurate predictions for mean flow and turbulent quantities, whereas the simulations with the K-epsilon model resulted in nonphysical and inconsistent turbulence predictions. Analysis of the three-dimensional flowfield simulation with the Reynolds-stress turbulence model shows that the shock structure downstream of the oblique barrel shock was a mirrored Image of the leeward side of the oblique barrel shock. Furthermore, the downstream location where vortical motion was initiated in the jet plume was caused by the recompression shock-induced vortices. These vortices were generated through the combined effects of the inflow air upwash behind the plume and the mirrored oblique barrel shock.