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Wing-tip vanes as vortex attenuation and induced drag reduction devicesAnalytical studies have been conducted to examine the feasibility of utilizing wing tip turbines to remove swirl from the wing trailing vortex, and hence reduce the potential for upset of following aircraft. Energy recovery from the turbines is also analyzed. A computer routine has been developed to permit rapid parametric studies of various tip turbine designs. It is shown that the optimum turbine is a non-rotating set of vanes which reduce swirl and recover energy in the form of reduced overall configuration induced drag. A specific case study indicates a 23% reduction in induced drag for a rectangular wing of aspect ratio 5.33, operated at a lift coefficient at 1.0.
Document ID
19760003924
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Wentz, W. H., Jr. (Wichita State Univ. Wichita, KS, United States)
Nagati, M. G. (Wichita State Univ. Wichita, KS, United States)
Date Acquired
August 8, 2013
Publication Date
January 1, 1975
Publication Information
Publication: Kansas Univ. Proc. of the NASA, Ind., Univ., Gen. Aviation Drag Reduction Workshop
Subject Category
Aircraft Design, Testing And Performance
Accession Number
76N11012
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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IDRelationTitle19760003909Collected WorksProceedings of the NASA, Industry, University, General Aviation Drag Reduction Workshop
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