The major object of this project is to research effect of viscosity on shock wave angle of supersonic inflow with a Computational Fluid Dynamics (CFD) as a commercial code. It will display of inviscid and five turbulence samples flow will be met the best of the published wind-tunnel experimentally by Lepicovsky et al [10]. Realizations founded on Fluent Inc as the CFD-Code and contain inviscid flow and the standard and Realizable k-ɛ, Spalart-Allmaras, Reynolds (Ensemble) Averaging and Large Eddy Simulation turbulent samples. A C-type grid is employed as a two-dimensional triangular to agree the researches mensuration at a 25o wedge at Mach-Number of 2.5 with 0.0° angle of attack. The results of numerical showed the samples flow fully prophesy the shock wave angle but the best results were at inviscid flow and then k-ε standard and realizable sample of flow, but Spalart-Allmaras, Reynolds (Ensemble) Averaging and Large Eddy Simulation. At supersonic flow the effect viscosity was slightly. The effect of viscosity showed on Drag, Lift Force Coefficients and skin friction distribution. The shock wave interaction with the boundary layer was clear.

The major object of this project is to research effect of viscosity on shock wave angle of supersonic inflow with a Computational Fluid Dynamics (CFD) as a commercial code. It will display of inviscid and five turbulence samples flow will be met the best of the published wind-tunnel experimentally b...