Abstract: A numerical study on the influence of forward-facing
cavity length upon forward-facing cavity and opposing jet combined
thermal protection system (TPS) cooling efficiency under hypersonic
flow is conducted, by means of which the flow field parameters, heat
flux distribution along the outer body surface are obtained. The
numerical simulation results are validated by experiments and the
cooling effect of the combined TPS with different cavity length is
analyzed. The numerical results show that the combined configuration
dose well in cooling the nose of the hypersonic vehicle. The deeper the
cavity is, the weaker the heat flux is. The recirculation region plays a
key role for the reduction of the aerodynamic heating.