Experimental study on the turbulent boundary layer of the hypersonic circular cone

In this paper to investment boundary layer transition characteristic with attack angle effect, an Experiment method was introduced to measure the hypersonic turbulence boundary layer parameters which used surface heat flux as basis to judge the boundary transition or not. The experiment was carried out in FD-20 piston gun tunnel at Mach number 6 using 5° half angle circular cone model. The nose tip radius and small attack angle effects on transition position on circular cone model were researched and attack angle effect transition curves were obtained at 2° and 3°. The test results showed that at small attack angle condition with increasing of angle of attack transition position move to bottom at windward and to nose tip at leeward in the boundary layer.