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The results of the joint experimental investigations and numerical simulations of hypersonic separated flows are presented. The computed and experimental results are compared with respect to surface pressure, skin friction and Stanton numbers distributions as well as the integral boundary layer parameters and the mean gas-dynamic profiles.The paper focuses on the problem of the mathematical modeling of Shock Wave / Turbulent Boundary Layer Interaction, which is of high importance for engineering applications. The case of the 2-D plane hypersonic flows (M=5) is selected for simulations, because it is closely related t o the problems of the space transport systems. The configurations of the incident shock wave interacting with flat plate boundary layer is simple, but gives a rather good test of the turbulence model and computational ability to predict the turbulent boundary layer separation and recovery phenomena.Three flow cases were studied with different shock generator angle (Y and hence, the different degree of flow separation, including the weak interaction case without separation (6" generator angle), the medium interaction case (10") with small separation zone and the strongest (14O) interaction case. The experimental data include the flowfield shadowgraphs, the pressure distributions along the plate surface, profile measurements in the section before and after the interaction [l] as well as the optical skin friction and heat transfer measurements "4. The computations were performed on the basis of the full unsteady 2-D Favre-averaged Navier-Stokes equations in strong conservation form closed by the Wilcox kw turbulence model [3]. The details of the method used in the computations can be found in [4].Figure l,a presents the experimental and computed pressure distributions along the plate surface for all three cases of generator angle and shows a good coincidence of the experimental (symbols) and computed (lines) distributions in the region of shock wave/ boundary layer interaction. In fig. l,b the computed and experimental skin friction distributions are compared. Note, that the open markers are for the velocity profile data and closed markers are for the data obtained using oil-film interferometer technique. Figure 1 demonstrates that the computations predict the skin friction distributions well except for the strongest interaction case, where the level of skin friction after the interaction is underpredicted. Figure 2 presents the comparison of the experimental and computed Stanton numbers. It should be mentioned that for (Y = 6" the computed results are in good agreement with the experiments but in the separated flow cases the computations overpredict the heat transfer level just after the reattachment point.The comparison of experimental and computed profiles of mean velocity, density and temperature were also performed showing a good agreement for the weak and medium interaction intensity, but rather poor fitness for the strongest case. Possible reasons of this disagreement may be the turbulence model ...