Hypersonic Turbulent Flow Simulation of Fire II Reentry Vehicle Afterbody

摘要

This paper presents a numerical investigation of the hypersonic reacting flow around the FIRE II reentry capsule.nAt the chosen freestream conditions, the forebody boundary layer and the separated flow on the afterbody arenturbulent. The Reynolds-averaged Navier–Stokes method along with two commonly used turbulence models arenused to compute the flowfield. Accurate prediction of turbulent separated flow at hypersonic conditions is challengingndue to the limitations of the underlying turbulence models. The presence of turbulent eddy viscosity in the flownsimulation results in a smaller separation bubble than the laminar solution at identical conditions. Also, the twonturbulence models predict different levels of eddy viscosity in the neck region. This has a dominant effect on thenseparation bubble size and the surface pressure. On the other hand, the eddy viscosity values in the near-wall regionndetermine the heat transfer rate to the body. The two models predict comparable heating rates on the conicalnfrustum, and the results match in-flight measurement well. By comparison, surface pressure predictions arenappreciably higher than the data.