Shock induced fluid structure interaction on a flexible wall in supersonic turbulent flow

Abstract

A detailed knowledge of the flow structure interaction in supersonic flows is important for the design of future space transportation systems. Therefore this work was devoted to the investigation of the shock wave boundary layer interaction on an elastic panel. During the wind tunnel experiments the panel deflection was measured with fast non-intrusive displacement sensors. On the flow side pressure, high-speed Schlieren photography and oil-film technique were used. The flow manipulation due to the panel deflection becomes manifest in a deformation of the impinging shock and the separation zone. The panel deflection consists of a constant and a dynamic component. The experimental results are discussed and compared to numerical results.