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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 3.—Axisymmetric SWBLI configurations.
Figure 6.—C-D nozzle schematic.
Figure 7.—C-D nozzle B.L. correction (R th  = 5.235 cm).
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