Computational Simulation of Turbulent Supersonic Flows around Axisymmetric Bodies Using a PNS/TLNS Multi-block Approach

In this work, turbulent supersonic flows over axisymmetric bodies, including the base, are investigated, using multi-block grid to solve the Navier-Stokes equations. Patched method has been used near the interfaces. Our numerical scheme was implicit Beam-Warming centeral differencing, while Baldwin-Lomax turbulence modeling was used to close the Reynolds averaged Navier-Stokes equations. In order to take advantage of structured grids, multi-block grid has been used widely in the past for complex geometries. On the other hand, different parts of such flow may require different forms of the governing equations. For supersonic flows over missile geometries, the thin layer Naveir-Stokes equations (TLNS) are usually used. But, the easiest and the fastest approach would be the use of parabolized Naveir-Stokes equations (PNS) everywhere. Note, for regions such as the missile’s blunt nose, near fins, and the base flow, we do not have to use the PNS equations. Therefore, this leads to the use of both TLNS and PNS equations with multi-block solution approaches. The resultes of this new version of our code (MBPTLNS), which is an extension of our original code (MBTLNS) [1], were compared with both computational and experimental benchmark data and showed close agreements.