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

The detailed structure of aerodynamic heating phenomena in three-dimensional shock wave/turbulent boundary layer induced by sweptback blunt fins are revealed by a new method developed by the authors. The new method is based on a new type of thin-film heat transfer gauge with high spatial resolution and fast response. Experiments are performed under the testing conditions of Mach number of 4, wall temperature condition T_w/T_O of 0.65 and Reynolds number of 1.2×10^-7. The sweptback blunt fins with semi-cylindrical leading edge in the plane normal to it are used for the present experiments. The results show that the extent of disturbed region decreases and the maximum peak pressure and heating rate decrease significantly as sweep angles of the fin is increased.