Computational simulation improvements of supersonic high-angle-of-attack missile flows

A numerical simulation is presented for the steady-state flow over a missil e body configuration for supersonic Mach number at incidence. The missile h as a diameter d of 0.09398 m and a length of 13d, Flow conditions specified are Mach 2.5, angle of attack 14 deg, and Reynolds number 1.23 x 10(6) bas ed on the diameter of afterbody to match experimental conditions. The three -dimensional Navier-Stokes equations in mass-averaged form were numerically integrated using both central and upwind difference methods, implicit Beam and Warming algorithm with the two-equation k-epsilon turbulence model to provide closure of the system of equations. The upwind method captured the crossflow shock better, and the central difference method predicted the vor tex shape and strength better. Modifications to the two-equation turbulence model, which limited the production of eddy viscosity for vortical Bows, w ere implemented to assess the improvement in accuracy. The modifications im proved prediction of the vortical shape and strength and showed improvement s in the surface pressure predictions due to stronger primary and secondary vortices. A grid resolution study to examine the effects of the modificati ons to the k-epsilon turbulence model was conducted. The grid study indicat ed that the improvements in the shear layer resolution and vortex core pred ictions were better when refinement was made in the body normal and circumf erential directions.