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An experiment is described that tests and guides computations of a shock-wave turbulent boundary-layer interaction flow over a 20° compression corner at Mach 2.85. Numerical solutions of the time-averaged NavierStokes equations for the entire flow field, employing various turbulence models, are compared with the data. Each model is evaluated critically by comparisons with the details of the experimental data. Experimental results for the extent of upstream pressure influence and separation location are compared with numerical predictions for a wide range of Reynolds numbers and shock-wave strengths.
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Horstman et al. (1977) studied this question.
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