Supersonic flow around a compression expansion corner using Implicit Steger and Warming flux vector splitting scheme. | Proceedings of 4th International Bhurban Conference on Applied Sciences and Technology 2005

Author(s)

Mansoor-Ul-Haq National Engineering and Science Commission (NESCOM), Islamabad, Pakistan

M. Zahid Bashir National Engineering and Science Commission (NESCOM), Islamabad, Pakistan

S. Bilal National Engineering and Science Commission (NESCOM), Islamabad, Pakistan

S. Zahir National Engineering and Science Commission (NESCOM), Islamabad, Pakistan

M. A. Khan National Engineering and Science Commission (NESCOM), Islamabad, Pakistan

Abstract

An inviscid flow pattern with in a channel containing a compression corner and an expansion corner at the lower surface and a straight upper surface is studied. An implicit formulation has been adopted. Steger and warming flux vector splitting scheme has been used. Pressure and density contours illustrating the formation of oblique shock, expansion wave and their reflection and interaction are shown for different Mach numbers. Pressure and density distributions along the lower wall have been compared to the analytical data. The results compare very well to the analytical solution.

Publication Details

Page(s) 133-146

DOI DOI not available

Published Journal: Proceedings of 4th International Bhurban Conference on Applied Sciences and Technology, Volume: 0, Issue: , Year: 2005

Keywords

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