Numerical Research on a New High Temperature Gas Wind Tunnel

A new ground test method using high temperature gas flow to simulate aerodynamic thermal environment of near space hypersonic vehicle is introduced. In the test section of the experiment equipment, the subsonic high temperature gas flow ejects the room temperature air to make the heat distribution of the experimental condition in line with that of the flight condition on the nose cap. The gas flow and heating characteristics of the test facility is simulated using FLUENT. The numerical study verified the feasibility of the experimental method and provided basis for further optimization according to the comparison of the temperature of the experimental condition with that in the real flight state on the same parts of the cap.