Investigation of the shock wave, boundary layer interaction of scramjet intake flows

This thesis aims to extend the knowledge of scramjet intake flows, especially of the SWBLI phenomenon under various free stream conditions and other influences. The SWBLI is considered particularly as it occurs in a wide range of flows spanning from the transonic over the supersonic to the hypersonic flow regime. These flows occur e. g. at the supercritical wing employed in modern aircrafts, the control surfaces of aircrafts and missiles flying at supersonic speeds as well as the re-entry vehicles like the Space Shuttle. The research on SWBLIs started more than sixty years ago and is still an important topic of the ongoing research. At present e. g. the heat load and the drag of a two-dimensional scramjet intake with a sharp leading edge could be estimated even with occurrence of a SWBLI provided that the size of the SWBLI is known. However, so far no analytical prediction method exists for the size of a SWBLI which depends on various flow similarity parameters (e. g. the Mach number), but a few correlations with a specific scope have been developed. These parameters change significantly for a space transportation system accelerating and passing altitudes with different atmospheric conditions. Due to the fact that the flow similarity parameters also affect the flow phenomena occurring e. g. at the outer compression ramps which also influence the SWBLI size, a thorough understanding of these phenomena and the flow similarity parameters of the SWBLI are required for the scramjet intake design.