The article introduced an experimental method using subsonic high-temperature-gas flow to simulate aerodynamic thermal environment of near space hypersonic vehicle.In the test section of the experiment equipment

the subsonic high-temperature gas flow ejected the room temperature air to make the heat distribution of the experimental condition in line with that of the real flight condition on the surface of the cap.Twelve experimental conditions were analyzed using FLUENT.The numerical analysis shows the temperature of the stagnation will below that of the gas flow

the inject ratio change of the facility can make a wide temperature change in the back region of the nose cone

so the facility is efficient to simulate the aerothermal environment of the hypersonic vehicle in a certain accuracy.