Shock Wave Capturing Numerically in Two Dimensional Supersonic Wind Tunnel for Different Configuration


Numerical solutions of two dimensional Euler equations are obtained fortransonic and supersonic flows. The shock capturing method is employed to solvecompressible Euler equations by using MacCormack's time marching method thatan explicit finite-difference technique. The test case chosen is that of a transonicand supersonic flow through a channel with a circular arc bump on the lower wall,half wedge and extended compression corner. Computational results accuratelyreproduced the flow field. In three cases, contour plots showing the importantfeatures of the flow-field are presented. The algorithm is tested for steady-stateinviscid flows at different Mach numbers ranging from the transonic to the supersonicregime and the results are compared with the existing numerical solutions. Themethod incorporates bounded high resolution of discontinuities and is therefore wellsuited to all flow regimes ranging from transonic to supersonic.