This paper focuses on the usage of the forward-facing cavity and opposing jet combinatorial configuration as the thermal protection system （TPS） for hypersonic vehicles. A hemispherecone nose-tip with the combinatorial configuration is investigated numerically in hypersonic free stream. Some numerical results are validated by experiments. The flow field parameters, aerodynamic force and surface heat flux distribution are obtained. The influence of the opposing jet stagnation pressure on cooling efficiency of the combinatorial TPS is discussed. The detailed numerical results show that the aerodynamic heating is reduced remarkably by the combinatorial system. The recirculation region plays a pivotal role for the reduction of heat flux. The larger the stagnation pressure of opposing jet is, the more the heating reduction is. This kind of combinatorial system is suitable to be the TPS for the high-speed vehicles which need long-range and long time flight.
To deal with the thermal protection of high speed vehicle, the cooling efficiency of a combinatorial thermal protection configuration which is composed of the forward-facing cavity and opposing jet is investigated. The numerical simulation result is validated by experiment and the flow field parameters, aerodynamic force and heat flux distribution are obtained. The detailed numerical simulation results show that this kind of combinatorial thermal protection configuration has an excellent effect on cooling the surface of the nosetip. By adding of the opposing jet with a small total pressure, it can avoid the disadvantage to the control performance of the aircraft which is caused by the cavity oscillating flow. And the low stagnation pressure is propitious to simplify the opposing jet system. The location of the recirculation region has a significant impact of the aerodynamic heating. The heat flux along outer body surface of the nosetip does not increase with the stagnation pressure of opposing jet decreases monotonically.
