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Numerical lifting line theory applied to drooped leading-edge wings below and above stallA numerical iterative solution to the classical Prandtl lifting-line theory, suitably modified for poststall behavior, is used to study the aerodynamic characteristics of straight rectangular finite wings with and without leading-edge droop. This study is prompted by the use of such leading-edge modifications to inhibit stall/spins in light general aviation aircraft. The results indicate that lifting-line solutions at high angle of attack can be obtained that agree with experimental data to within 20%, and much closer for many cases. Therefore, such solutions give reasonable preliminary engineering results for both drooped and undrooped wings in the poststall region. However, as predicted by von Karman, the lifting-line solutions are not unique when sectional negative lift slopes are encountered. In addition, the present numerical results always yield symmetrical lift distributions along the span, in contrast to the asymmetrical solutions observed by Schairer in the late 1930's. Finally, a series of parametric tests at low angle of attack indicate that the effect of drooped leading edges on aircraft cruise performance is minimal.
Document ID
19810031477
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Anderson, J. D., Jr.
(Maryland, University College Park, Md., United States)
Corda, S.
(Maryland Univ. College Park, MD, United States)
Van Wie, D. M.
(Maryland Univ. College Park, MD, United States)
Date Acquired
August 11, 2013
Publication Date
December 1, 1980
Publication Information
Publication: Journal of Aircraft
Volume: 17
Subject Category
Aerodynamics
Accession Number
81A15881
Funding Number(s)
CONTRACT_GRANT: NSG-1570
Distribution Limits
Public
Copyright
Other

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