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Technical Note

Effects of taper ratio on trailing vortex structure

Published online by Cambridge University Press:  04 July 2016

L. W. Traub
L. W. Traub*
Affiliation:
Aerospace Engineering DepartmentTexas A&M UniversityTexas, USA
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Abstract

A theoretical study was undertaken to determine the effect of taper ratio on the trailing vortex structure of a high aspect ratio unswept wing. The wing was modelled using lifting line theory, and the vortex was assumed to have a Rankine distribution of circulation. The results show that reducing the taper ratio of the wing, decreases the maximum tangential velocity of the vortex as well as the vortex span while the core's diameter increases. Data is also presented showing the sensitivity of induced drag to wake vortex parameters.

Type
Research Article
Information
The Aeronautical Journal , Volume 100 , Issue 996 , July 1996 , pp. 252 - 254
Copyright
Copyright © Royal Aeronautical Society 1996 

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References

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