An experimental investigation of heat transfer phenomena in shock wave/ boundary layer interaction at Mach 6

This paper aims to experimentally investigate the thermal effects associated with shock wave/boundary layer interaction (SWBLI) at a Mach number of 6. Schlieren and temperature sensitive paint techniques were employed for flow visualization. Quantitative data on temperature rise and Stanton number distribution is provided. In weak SWBLI, the maximum temperature on the flat plate exceeded 40 K, while in strong SWBLI, it exceeded 50 K. It reveals the effect of interaction zones in streamwise positions on the peak heat flux and their physical mechanisms under different shock wave intensity and Reynolds number conditions. A distinctive pattern of streamwise heat flux bi-peaks is presented, which differ under weak and strong SWBLI conditions. Additionally, a link between the spanwise heat flux and vortex structure distributions is uncovered. This research provides important insights into the mechanics underlying the thermal impacts of SWBLI, which are crucial for the design and optimization of thermal protection systems in aeronautical engineering.