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Shock-shock, shock-vortex interaction and aerodynamic heating in hypersonic corner flow

Part of:75 year anniversary of Aeronautical Engineering at Glasgow University

Published online by Cambridge University Press:  04 July 2016

Ning Qin,
Karl W. Scriba and
Bryan E. Richards
Ning Qin
Affiliation:
Department of Aerospace Engineering, University of Glasgow
Karl W. Scriba
Affiliation:
Department of Aerospace Engineering, University of Glasgow
Bryan E. Richards
Affiliation:
Department of Aerospace Engineering, University of Glasgow
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Summary

A symmetric Mach 12·76 hypersonic flow in a 90° corner, formed by 30° swept back intersecting 8° wedges, was investigated in detail through numerical simulation using locally conical Navier-Stokes equations. Three different numerical schemes for spatial discretisation, MacCormack central differencing, van Leer’s flux vector splitting and Osher’s flux difference splitting, were studied to compare their capabilities to capture both strong shock waves and thin shear layers. Comparison with experimental data was made to validate the simulation. The numerical simulation provided further insight into the flowfield and a pair of counter-rotating vortices were discovered near the junction of the corner.

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 95 , Issue 945 , May 1991, pp. 152 - 160
Copyright
Copyright © Royal Aeronautical Society 1991 

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