Detailed pitot, static, and wall pressure measurements have been obtained for a transonic normal shockwave/turbulent boundary-layer interaction at freestream Mach numbers of 1.28, 1.37, and 1.48, and at a constant unit Reynolds number of 4.92xl0 6/m in an axisymmetric, internal flow. Measurements have also been obtained at a unit Reynolds number of 9.84xl0 6/m at a freestream Mach number of 1.29. The interaction depends very strongly on the Mach number. The effect of Reynolds number on the unseparated interaction is small. Flow blockage due to the wind tunnel wall boundary layer produces a weaker interaction and a much larger supersonic tongue than observed for planar flows. Comparisons are made with solutions to the timedependent, mass-averaged, Navier-Stokes equations incorporating a two-equation, Wilcox-Rubesin turbulence model. The computations are in agreement with the experimental results.
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Om et al. (1985) studied this question.
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