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CFD Validation Experiment of a Mach 2.5 Axisymmetric Shock-Wave Boundary-Layer Interaction

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Figure

Figure 1. M=2.0 oblique SWBLI oil flow.
Figure 4. Section view of W6B test facility.
Figure 7. C-D nozzle B.L. correction (R th =5.235 cm).
Figure 8. Test section schematic.
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