Aerodynamic heating in shock wave/turbulent boundary layer interaction regions induced by blunt fins

A study on aerodynamic heating in the interaction regions of shock waves and turbulent boundary layers induced by blunt fins with semicylindrical leading edge is performed under the conditions of Mach number of 4, total pressure of 1.2 MPa, the ratio of wall temperature to total temperature of 0.66 and Reynolds number of 1.3×10⁷. The blunt fins of leading edge diameters of 6 mm and 10 mm are used to examine the influence of leading edge diameter on the pressure and heat transfer rate distributions. Flow fields are visualized by the Schlieren method and oil flow technique. Also the detailed distributions of surface pressure and heat transfer rate are measured in the entire interaction regions. The results show that two significant peaks are observed in the distributions of surface pressure and heat transfer rate.