Shock wave capturing numerically in two-dimensional supersonic wind tunnel for different configurations

Abstract EN

Numerical solutions of two dimensional Euler equations are obtained for transonic and supersonic flows.

The shock capturing method is employed to solve compressible Euler equations by using McCormack's time marching method that an explicit finite-difference technique.

The test case chosen is that of a transonic and supersonic flow through a channel with a circular arc bump on the lower wall, half wedge and extended compression corner.

Computational results accurately reproduced the flow field.

In three cases, contour plots showing the important features of the flow-field are presented.

The algorithm is tested for steady-state in viscid flows at different Mach numbers ranging from the transonic to the supersonic regime and the results are compared with the existing numerical solutions.

The method incorporates bounded high resolution of discontinuities and is therefore well suited to all flow regimes ranging from transonic to supersonic.