Study on three-dimensional shock wave/turbulent boundary layer interaction induced by sweptback sharp fins at supersonic flow

Shock wave/turbulent boundary layer interaction regions induced by sharp fins with sweptback angles have been experimentally investigated. Experiments are performed under the condition of Mach Number of 4, total pressure of 1.2 MPa, total temperature of 280 K and Reynolds Number of 2.7×10⁷. First of all, surface flows are visualized by oil flow technique, then surface pressure distributions are measured for various sweptback angles of 0°, 15°, 30° and 45°. The major objective of this study is to investigate effect of sweptback angle of the leading edge of fin on the interaction regions of flow fields. The results show the effect of sweptback angle of the leading edge are quite significant on reducing interaction region and peak pressure. Also the effect of the shape of fin is investigated by comparing the present results with the previous of blunt fins conducted by present authors. These results also show the effect of shape of the leading edge are quite significant in reducing interaction region and peak pressure.