Aerodynamic heating in the interaction regions of shock waves and turbulent boundary layers induced by sharp fins

A study on aerodynamic heating in the interaction regions of shock waves and turbulent boundary layers induced by sharp fins 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 0.63-0.66 and Reynolds number of 1.2×10⁷. Attack angles of fins are selected as 4, 10 and 16 degrees to investigated the cases of incipient, primary and secondary separation of the boundary layers. Surface flow patterns are visualized by oil-flow technique. The detailed distributions of surface pressure and heat transfer rates are measured in the entire interaction regions. For the measurements of the heat transfer rates, a new type of multi-layered thin-film heat-transfer gauge is developed by the present authors. The results show that the distributions of surface pressure and heat transfer change drastically as the attack angles of fins are increased. In separated cases the peak heatings occur along the primary reattachment lines.