Aeroheating Experiment for Airbreathing Hypersonic Vehicle

To obtain aeroheating environment data of airbreathing hypersonic vehicle,aeroheating experiment had been conducted in shock wave wind tunnel.The test was carried at Mach number 6.12 and unit Reynolds number Re/L=1.37×10~7(1/m) with a 1/4 sub-scale model.The heat flux distribution at nose lead edge,nose upper/lower edge,airframe upper/lower centerline,body section outline,wing/fin lead edge were obtained.Results showed nose lead edge,airframe lower surface,inlet lip lead edge and wing/fine suffered rigorous aeroheating environment,and configuration of waveraider influences heat flux distribution.