Numerical simulation of two-dimensional steady state compressible laminar flow fields around sabot configuration is presented. The numerical scheme adopted in this study is the Weighted Average Flux (WAF) method. The WAF method acheives second order accuracy in space and time by using the conventional piecewise constant data Riemann problem. This study includes finite volume formulation of the WAF method with its TVD property.
Four test problems are solved for validation of this code. They are one-dimensional time dependent shock tube problem, steady state inviscid as well as viscous flow fields around NACA0012 airfoil, and laminar flow field around circular cylinder which includes supersonic near-wake behaviour.
Computation around a sabot configurarion is performed at free stream Mach numbers 2, 3, 4.5 and its results are compared with the inviscid result. The result at free stream Mach number 4.5 is compared with the wind-tunnel experimental data.