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  • Supersonic Flow Over a Wedge - Numerical Results

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Next, click on print information icon , and click anywhere behind the shock. This will display a range of values. For instance, I received 2.2354529, 2.2513809. These range of values match well with the analytic solution we received in the pre-anaysis (Mach no. = 2.54254, 0.8% difference)

Pressure Coefficient Contours

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