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The performances of K-ω SST(Shear-Stress Transport) turbulence model and high order low dissipative Flux difference scheme of Roe are evaluated against experimental flow fields at different geometries and angle of attacks at supersonic mach no. The numerical predictions include lift, drag and pitching moment coefficients at different angle of attacks. Most significantly, this research provides a sensitivity study on the accuracy of the solutions with respect to the effects of free stream turbulence, grid resolution, grid spacing near the wall, initial conditions, numerical methods and free stream Mach number effects on compressible flows. Comparison of two geometries, cone cylinder and cone cylinder with fins is provided in order to study the effects on the aerodynamics characteristics by the addition of the lifting surfaces and the same is compared with the available experimental data. For the present study supersonic flow is simulated at Mach number 4 and the angle of attack is varied.