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Application of the vortex breakdown phenomenon in the attenuation of trailing vortices

Published online by Cambridge University Press:  04 July 2016

L. W. Traub ,
S. Mani ,
S. F. Galls  and
O. K. Rediniotis
L. W. Traub
Affiliation:
Aerospace Engineering Department , Texas A&M University Texas, USA
S. Mani
Affiliation:
Aerospace Engineering Department , Texas A&M University Texas, USA
S. F. Galls
Affiliation:
Aerospace Engineering Department , Texas A&M University Texas, USA
O. K. Rediniotis
Affiliation:
Aerospace Engineering Department , Texas A&M University Texas, USA
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Abstract

An experimental investigation to determine the effectiveness of a wing-tip device designed to attenuate the trailing vortex of a lifting, flat-plate wing is detailed. The induced-breakdown vortex attenuation device (IBVAD) is essentially a toed-in, vertically-oriented sheared tip. Results are presented comprising force-balance, water tunnel flow visualisation and wake studies using a seven hole probe. The data shows that compared with an equal span rectangular wing, variations of the IBVAD device can reduce drag at moderate-to-high lift coefficients, as well as reduce die maximum rotary velocity of the trailing vortex by 28%. Axial vorticity in the wake vortex was significantly attenuated compared with the rectangular wing, with a 52·6% reduction in the magnitude of die maximum vorticity. The vortex core radius was also seen to be larger than die rectangular wing. However, even substantial attenuation and redistribution of trailing vorticity may be insufficient to reduce the wake hazard.

Type
Research Article
Information
The Aeronautical Journal , Volume 102 , Issue 1018 , December 1998 , pp. 439 - 444
Copyright
Copyright © Royal Aeronautical Society 1998 

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