Hypersonic Shock Wave Boundary Layer Interaction Studies on a Flat Plate at Elevated Surface Temperature

Abstract

Experimental shock wave boundary layer interactions (SWBLI) on a flat plate model with deflectable flap and variable surface temperature were studied in the DLR High Enthalpy Shock Tunnel Göttingen (HEG) at Mach 7.4 and 6.65x106 m−1 unit Reynolds number. The wind tunnel model used in the scope of the study was equipped with an internal heating element allowing for variable surface temperatures up to 800 K. The model consists of an unheated flap which can be deflected in the range of 0◦, 15◦ and 30◦, a heatable flat plate and an exchangeable leading edge. The latter is passively heated through the contact to the heated model section. At the hinge line a gap of 0.2 mm was realized between the flap and flat plate. In the scope of the study the effects caused by leading edge bluntness, flap deflection angel, gap opening and surface temperature on the shock wave boundary layer interaction were investigated. Additional attention was paid to the laminar turbulent boundary layer transition process.