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Reduction of wing rock amplitudes using leading-edge vortex manipulationsA mechanically operated leading edge flap system was used to perturb leading edge vortex position on a free-to-roll double-delta wing. The motion of the flaps was synchronized with the wing rolling oscillations and the effect of the phase shift between the oscillations of the wing and the flaps was investigated. Experimental results indicated that this simple approach was effective in reducing the amplitude of the unintended rolling motion and its implementation to actual airplane configurations is rather simple.
Document ID
19920043109
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Walton, James
(NASA Ames Research Center Moffett Field, CA, United States)
Katz, Joseph
(San Diego State University CA, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1992
Subject Category
Aircraft Stability And Control
Report/Patent Number
AIAA PAPER 92-0279
Accession Number
92A25733
Funding Number(s)
CONTRACT_GRANT: NCC2-458
Distribution Limits
Public
Copyright
Other

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