In order to reduce the size of coolant supply system of opposing jet in hypersonic vehicles, the fuel gas generating with solid fuel was adopted as an opposing jet. The RANS (reynolds-average navier-stokes) equations coupled with the Menter′s SST (shear stress transport) model was employed to solve the opposing jet flow field of hypersonic hemisphere model. The typical results have been validated with experiments performed in the literature. The influence of the high temperature fuel gas on the hemisphere model thermal protection characteristics was analyzed with different flying condition. Results show that the high temperature fuel gas weakens the heat flux reduction of opposing jet, but the peak heat flux exhibits a prominent reduction in contrast to that without injection.The cooling efficiency can be strengthened by increasing the jet pressure. With a reasonable jet pressure, the similar cooling efficiency can be obtained compared with that of the normal coolant and it does not result in additional mass flux. Moreover, the three solid fuel and its combustion temperature are listed. For high Mach flying which is higher than 6, the solid fuel can provide required jet temperature for opposing jet thermal protection system.