Experimental Study of Flow on the Leeward Side of a Cone at a High Angle of Attack Based on Temperature Sensitive Paint

In the hypersonic flow of a cone at a high angle of attack, there will be complex flow phenomena, such as flow separation, crossflow vortices and boundary layer transition. The flow phenomena will affect the temperature distribution on the cone surface significantly. The temperature rise distribution results on the cone leeward surface with an attack angle of 10° were obtained from the temperature sensitive paint system in Mach 6 hypersonic low turbulence wind tunnel. Through the experimental results, complex flow law and its influence on the distribution of surface temperature were discussed. With the analysis of temperature rise distribution curves at different positions and different azimuth angles, the development process of the flow on the conical leeward surface and the flow characteristics at different development stages were discussed. By adjusting the total pressure of the incoming flow, the temperature rise distribution results with different Reynolds numbers were obtained, and the influence of Reynolds number on the flow was summarized. Results show that the laminar separation, stationary crossflow vortices, boundary layer transition, turbulent separation and reattachment would occur in sequence during the development of the boundary layer flow on the leeward surface. As the Reynolds number decreases, the range of laminar flow and the range of stationary crossflow vortices increase, and the range from the observation of the stationary crossflow vortices to the beginning of transition is basically the same.