Aeroheating Experiment for Airbreathing Hypersonic Vehicle
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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.