Shock Wave/Boundary Layer Interactions Induced by a Rhombic Delta Fin

This paper presents an experimental and numerical study of shock wave/turbulent boundary layer interaction induced by rhombic delta fins placed on the side wall of the test section. The experiments were carried out in 80×100mmmm2 supersonic wind tunnel at free stream Mach number of 2.50. Corresponding free stream unit Reynolds number was 3.74×107/m. Five models were used in this study. The fin half apex angles were 12°, 18°, 24° at 30° sweepback angle and for the fin sweepback angles 15°, 45° at 18° half apex angle. Schlieren photographs, oil flow measurements and wall surface static pressure measurements were made. It was found that the upstream influence line runs parallel to the primary separation line and obeys the Reynolds number scaling law. Furthermore, the primary separation angle βs1 can be accounted for by referencing βs1 and β0 to Mach angle μ∞.