Aerothermal simulations of a multimaterial cone at Mach 22

The ability to predict boundary layer transition is critical to obtaining an accurate estimation of heat transfer in hypersonic flows. Perturbation methods used to predict transition require a good base flow to provide correct results. This study uses a 2D axisymmetric simulation to model the re-entry of a 22-degree cone at Mach 22 and obtain a base flow for future stability analyses. A coupled approach is used, with a finite volume fluid solver (HEGEL) and a finite element ablative solid solver (CHyPS) connected using a coupling library (preCICE). HEGEL uses an 11-species air model and accounts for the NLTE (non-local thermal equilibrium) effects in the flow. CHyPS is used to model the thermal response of a multi-material cone composed of a graphite nose, quartz spacer and beryllium afterbody. The re-entry process is simulated and the results are validated by comparing flow parameters and cone surface temperatures to values from literature.