STORT flight experiment - Fin-Induced Shock Boundary Layer Interactions.

Fin-induced Shock Wave Boundary-Layer Interaction (SBLI) experiments have been conducted in a Mach 5 laminar boundary layer. The tests have been conducted in the Indraft Supersonic Wind Tunnel (ISWT) at the University of Arizona at an Re_θ of approximately 1100. The purpose of this research is to characterize a fin-induced SBLI in support of the DLR STORT Program. Experiments are performed on the planar wall of the wind tunnel to investigate the influence of the fin's finite geometry (including moderate bluntness and expansion fans). In addition, these tests support other experiments conducted on a hollow cylinder to assess the influence of base curvature. The state of the boundary layer and key features of the flow topology have been identified and measured. Oil flow visualization and high-speed schlieren have been used to characterize fin-induced separation and vortex structures. The investigation is further supported with unsteady wall-pressure measurements in key regions of the fin-induced flow. This research improves the understanding of complex fin-induced SBLIs and will be used to augment studies on the larger hollow-cylinder model and the flight geometry.