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At the German Aerospace Center (DLR), a possible solution for handling extreme aerothermodynamic heat loads has been investigated. The solution involves an innovative new way of transpiration cooling, using liquid water. The concept has been tested at the arc heated wind-tunnel section of DLR. The test campaign will be described and the results will be compared with transpiration cooling using a gas as a coolant.

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Since escalating §uid structure interactions (FSI) can cause a complete loss of a spacecraft, a detailed knowledge of the mechanisms of §ow structure interactions in supersonic §ows is important for the design of future space transportation systems. The ¦rst 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 de §ection was measured with fast nonintrusive displacement sensors. On the §ow side pressure, high-speed Schlieren photography and oil-¦lm technique were used. The §ow manipulation due to the panel de §ection becomes manifest in a deformation of the impinging shock and the separation zone. The panel de §ection consists of a constant and a dynamic component. The experimental results are discussed and compared to numerical results.

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