20 February 2017 The effect of wedge position and inlet geometry on shock wave reflection
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Proceedings Volume 10328, Selected Papers from the 31st International Congress on High-Speed Imaging and Photonics; 103281G (2017) https://doi.org/10.1117/12.2269003
Event: 31st International Congress on High-Speed Imaging and Photonics, 2016, Osaka, Japan
Abstract
Experiments were conducted in a shock tube to determine the effect of planar wedge inlet geometry on the shock wave reflection pattern that occurred on a wedge. High-speed schlieren imaging was used to visualize the experiments conducted in air with a nominal incident shock strength of Mach 1.31. The experimental test pieces consisted of a wedge mounted above the floor of the shock tube where the underside wedge angle was varied. The upper wedge angle was fixed at 30°, resulting in a Mach reflection. The underside wedge angle was either 30° or 90°, corresponding to a conventional and blunt wedge respectively. For the cases presented here, the reflected shock from the initial interaction reflects off of the shock tube floor and diffracts around the wedge apex. A density gradient is formed at the wedge apex due to this process and results in a vortex being shed for the 90° wedge. It was shown by simple measurements that the diffracted wave could reach the triple point of the upper Mach reflection if the wedge were of sufficient length.
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R. E. Hall, N. P. da Silva, B. W. Skews, R. T. Paton, "The effect of wedge position and inlet geometry on shock wave reflection", Proc. SPIE 10328, Selected Papers from the 31st International Congress on High-Speed Imaging and Photonics, 103281G (20 February 2017); doi: 10.1117/12.2269003; https://doi.org/10.1117/12.2269003
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