A previously developed pressure based calculation procedure for incompressible flows was modified and applied to transonic and supersonic flows. It uses pressure as a primary variable in preference to density and body fitted coordinate and non-stagger...
A previously developed pressure based calculation procedure for incompressible flows was modified and applied to transonic and supersonic flows. It uses pressure as a primary variable in preference to density and body fitted coordinate and non-staggered grid system. The discretized momentum equations were rearranged as a system of equations with respect to covariant velocity components. Three different discretization schemes, QUICK, hybrid and first order upwind, were used to approximate the convective terms and compared. Present approach was tested for two transonic flow and one supersonic flow problems. Comparison with previous results show that present approach can be used as a solver for compressible flows.