Abstract: To study the characteristic of aerodynamic heating on common aviation vehicle(CAV) from near continuous flow region to rare transitional flow one, the surface aerodynamic heat flux distribution on CAV was measured in the ground test with infrared thermographic technique under the typical orbital parameter conditions. The function and parameter of hypersonic low density wind tunnel and infrared camera as well as the shape characteristic of the CAV were given in this paper firstly. Three simulation means such as viscous interaction parameter, enthalpy difference between total enthalpy and wall enthalpy and Knudsen number parameter adopted in the hypersonic low density wind tunnel were presented. At the test conditions M=7, =0, 12 and M=12, =24, heat transfer distributions on the whole model surface, typical flow field schlieren pictures and infrared mappings were obtained. The heat transfer results at the model windward centerline, windward wing forward edge and theoretical computation were compared at different Mach number and different attack angle. Test result shows that heat flux distributions on windward wing forward edge possesses of shape as saddle, that the influence of the variety of attack angle on aerodynamic heating is distinct.