Numerical analysis of high-temperature-gas wind tunnel thermal characteristics

An experimental method using subsonic high-temperature gas flow to simulate aerodynamic thermal environment of near space hypersonic vehicle was introduced. In the test section of the experiment equipment, the room temperate air was ejected by the subsonic high-temperature gas flow to make the heat distribution of the experimental condition in line with that of the real flight condition on the cap. 13 experimental conditions were analyzed using computational fluid dynamics(CFD). The numerical analysis verifies the feasibility of the experimental method and provides basis for demonstration of the experiment facilities.