In the framework of the NATO-RTO-AVT-WG10 entitled "Technologies for Propelled Hypersonic Flight", base flow test cases have been selected for code validation. Concerning the first dataset devoted to base flowplume interaction at moderate nozzle pressure ratios, the influence of numerical discretization technique and turbulence models are discussed. The multi-dimensional upwind (MDU) discretization technique on unstructured grids applied to the axisymmetric base flow model with an underexpanded jet predicts base pressures that are consistently lower than the experimental values. If no proper conclusions can be drawn from this comparison because of the 3-D model support influence in the experiments, conclusions in relation to the turbulence models and to the axisymmetric results of the other code, the finite-volume technique on multiblock grids (LORE), may be of interest. Concerning the second dataset of a boattailed afterbody flowfield with plume-induced-separation, RANS calculations with transport equations turbulence models reproduce the general organization of the flow, in particular the free separation phenomenon with a X-shock system induced by the jet/external flow interaction. The afterbody wall-pressure profile on the cylindrical part and during the expansion wave is well restituted. But it seems difficult to predict accurately the afterbody wall-pressure profile on the boat-tail because turbulence models have difficulties to reproduce positive pressure gradients. Calculations do not reveal the existence of a singular reflection on the symmetry axis for the recompression barrel shock of the propulsive jet, with a Mach disc, as it has been experimentally observed.
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