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Experimental and numerical Investigation of wind tunnel wall interference near Mach one

Published online by Cambridge University Press:  04 July 2016

M. Mokry ,
M. Khalid ,
Y. Mébarki  and
A. Rebaine
M. Mokry
Affiliation:
Institute for Aerospace Research, Ottawa, Canada
M. Khalid
Affiliation:
Institute for Aerospace Research, Ottawa, Canada
Y. Mébarki
Affiliation:
Institute for Aerospace Research, Ottawa, Canada
A. Rebaine
Affiliation:
Institute for Aerospace Research, Ottawa, Canada
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Abstract

Surface pressure measurements on the CAST-10-2/DOA 2 aerofoil, conducted in the IAR l.5m wind tunnel and supported by CFD simulations, are used to validate some new theoretical analyses of transonic wall interference. Based on the transonic freeze principle, it is shown that the stream Mach number correction is indeterminate near Mach one.

Type
Research Article
Information
The Aeronautical Journal , Volume 105 , Issue 1052 , October 2001 , pp. 589 - 596
Copyright
Copyright © Royal Aeronautical Society 2001 

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