EXPERIMENTAL ANALYSIS OF HYPERSONIC INLET BUZZ AT MACH 5

The present thesis work is focused on the experimental investigation of the hypersonic inlet buzz at Mach 5. The tests were performed in the High Supersonic Wind Tunnel at the University of Manchester. On the basis of previous experimental campaign and numerical simulation, both performed on the same inlet model, new tests were conducted with the adoption of Schlieren and Shadowgraph imaging techniques and Fast-Responding Pressure Sensitive Paints, in order to gain a better insight into the inlet buzz phenomenon at the determined flow regime. Two inlet configurations have been tested and compared. The first one was the design point configuration and the second was the unstarted inlet condition in which buzz ensued. The collected data were analysed with conventional and Data-Driven Modelling Methods. The results revealed the capability of Fast-Responding Pressure Sensitive Paints to detect the buzz phenomenon and the coherent structures that form this flow instability. The employment of the Fast-Responding Pressure Sensitive Paints is a method not yet fully deployed by scientific research on this specific test case. Therefore, this study has the aim to be a baseline for future further investigations related to the inlet buzz phenomenon using this technology.