Numerical Simulation of Planetary Reentry Aeroheating Over Blunt Bodies with Non-Equilibrium Reacting Flow and Surface Reactions

*† Thermal protection layer has been commonly used to protect the reentry vehicles from the harsh conditions encountered at hypersonic velocities. Numerical simulations and experiments are used to predict the amount of this protective layer needed so that vehicles safely traverse the harsh zone. Prediction of ablation requires modeling of hypersonic flows coupled with reacting gas chemistry and the response of the solid protection layer to the extreme conditions. Current computational codes modeling chemistry with hypersonic flow are coupled with codes predicting the response of the protection layer. In addition there has been limited study on effects of chemical Nonequilibrium in flow the field and surface ablation on laminar-turbulent flow transition of hypersonic boundary layers. Such an integrated tool would facilitate the study of transition in chemically reacting ablative flow fields. Therefore it is our aim to develop an integrated high order code which solves the material response along with the flow with thermal and chemical non equilibrium with species ionization. In this paper we present results of shock capturing nonequilibrium solver with surface reactions for modeling ablation. The code has 11 species reaction model to account for carbon species.