Computation of hypersonic shock boundary layer interaction on a double wedge using a differential Reynolds Stress Model

The simulation of hypersonic flows presents some difficulties due to the interaction between boundary layers and shock waves and to the high total enthalpy. In order to achieve more accurate numerical results with respect to physics, a Reynolds stress model (RSM) has been implemented in the well validated Reynolds averaged Navier-Stokes solver QUADFLOW. The RSM developed and tested by Eisfeld, showed promising results on structured grids. It is a combination of two RSM: one that performs better near the wall and another able to achieve good results in the far field. The implementation consisted of writing new routines for the source terms and their derivatives as well as modifying routines for the computation of viscous fluxes, boundary conditions and far field conditions. The newly implemented model has been tested and validated on the standard test case of a subsonic flat plate and on a hypersonic configuration. The results show a good agreement between the experimental data and the solutions obtained with standard turbulence models implemented in the same software. A grid convergence study and a simulation on a complete three dimensional inlet are being performed.