Investigation on the effectiveness of transpiration cooling under the influence of shock wave

Abstract

As an advanced active cooling method, transpiration cooling can be used for thermal protection of high-temperature wall. The change of cooling effect caused by the incident shock wave on the transpiration cooling boundary layer is sufficient to affect the safe flight of the aircraft. In this paper, the interaction mechanism between shock wave and transpiration cooling is studied based on the thermal equilibrium model. The effects of shock wave incident angle, coolant injection ratio, Mach number of high enthalpy airflow and coolant type on thermal protection effect were studied respectively. Shock wave incidence in the boundary layer of transpiration cooling can cause the change of coolant flow and heat sink distribution in porous media, and cause the fluctuation of fluid parameters in the boundary layer. The temperature inhomogeneity on the porous wall and the inhomogeneity of the total enthalpy difference are markedly affected by the shock wave intensity. The heat insulation effect of the coolant on the solid surface limits the improvement effect of the increase of the injection ratio on the effective heat absorption power. Hydrogen as a coolant can form a better cooling effect and has less resistance to the mainstream.