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Published on Sep 30, 2009
Two short-duration clips from the UT Arlington Aerodynamics Research Center supersonic wind tunnel are shown in this video. Each shows different views of Mach 2.5 flow over a flat plate with a 5 degree wedge near the end of the viewing area. The flow is from right to left. A portable Schlieren system is used for the resulting oblique shock wave visualization. Although there appear to be many shock waves during these tests, those not attached to the wedge are called Mach lines and do not cause large pressure differences before and after the discontinuity.