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Further analysis of self-induced roll oscillations of a non-slender delta wing

Published online by Cambridge University Press:  03 February 2016

M. E. Beyers  and
L. E. Ericsson
M. E. Beyers
Affiliation:
Institute for Aerospace Research, Ottawa, Ontario, Canada
L. E. Ericsson
Affiliation:
Mountain View, California, USA
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Abstract

In low-speed wind tunnel tests at α = 25 and 30º of a 45º delta wing with semicircular leading edges limit cycle oscillations occurred around the 50º roll trim angle. In some cases the oscillations were highly regular, in other cases, highly irregular. An analysis of the observed roll-oscillation dynamics has shown that several viscous flow phenomena are involved, which depend strongly on the leading-edge geometry, and whose relative importance can vary dramatically with the existing Reynolds number in critical flow regions. The possible role of surface roughness in modifying the viscous flow/motion coupling to cause these dramatically different test results is examined.

Type
Research Article
Information
The Aeronautical Journal , Volume 110 , Issue 1113 , November 2006 , pp. 739 - 748
Copyright
Copyright © Royal Aeronautical Society 2006 

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