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

Since escalating fluid-structure interactions (FSI) can cause a complete loss of a spacecraft, a detailed knowledge of the mechanisms of flow-structure interactions in supersonic flows is important for the design of future space transportation systems. The first step is to analyze the basic mechanisms at a generic test case that is ascertainable also with high quality simulations. 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 nonintrusive 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