Shock induced fluid structure interaction on a flat plate in supersonic turbulent flow

Abstract

For the development of new lightweight structures for space transportation systems a comprehension of the fluid structure interactions in supersonic flows is necessary. Therefore this is one of the main topics of the Collaborative Research Centre Transregio 40. A first experimental study concentrating on the mechanical aspects of a fluid structure interaction was performed at the German Aerospace Center (DLR) in Cologne. The generic model used in this study allows to investigate the fundamental problem of the shock wave impingement on a turbulent boundary layer and the resulting structure deformation. So it combines the aspects of compressibility, flow separation, turbulence and aeroelasticity. To facilitate a comparison with detailed simulations big attention was paid to the characterization of the free stream flow and to achieve a fully developed turbulent boundary layer flow. With a Laser-2-Focus Velocimeter the turbulent intensity was measured at several positions in the stream. The boundary layer flow was characterized using a miniature Pitot-rake. The pressure distribution of the shock-boundary-interaction was measured with static PSI-sensors. During the experiments with structure deformation high-speed Schlieren photography, fast pressure sensors, fast non-intrusive displacement sensors and oil-film technique were employed. The results of these experiments will be presented at the conference.