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A vortex-lattice method for general, unsteady aerodynamicsA general method of calculating unsteady, incompressible, inviscid, three-dimensional flows around arbitrary planforms has been developed. The method is an extension of the vortex-lattice technique. It is not limited by aspect ratio, camber, or angle of attack, as long as vortex breakdown does not occur above the surface of the wing and separation occurs only along sharp edges. As the wing performs arbitrary maneuvers, the position of the wake and the distribution of circulation on the wing and in the wake are obtained as functions of time. One desirable feature of the present method is its ability to treat steady lifting flows very efficiently. Several examples of steady and unsteady flows are presented. These include rectangular wings, with and without flaps, delta, and cropped delta wings.
Document ID
19850036360
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Konstadinopoulos, P.
(Virginia Polytechnic Inst. and State Univ. Blacksburg, VA, United States)
Thrasher, D. F.
(Virginia Polytechnic Inst. and State Univ. Blacksburg, VA, United States)
Mook, D. T.
(Virginia Polytechnic Inst. and State Univ. Blacksburg, VA, United States)
Nayfeh, A. H.
(Virginia Polytechnic Inst. and State Univ. Blacksburg, VA, United States)
Watson, L.
(Virginia Polytechnic Institute and State University Blacksburg, VA, United States)
Date Acquired
August 12, 2013
Publication Date
January 1, 1985
Publication Information
Publication: Journal of Aircraft
Volume: 22
ISSN: 0021-8669
Subject Category
Aerodynamics
Accession Number
85A18511
Funding Number(s)
CONTRACT_GRANT: N00014-79-C-0103
CONTRACT_GRANT: NSG-1262
Distribution Limits
Public
Copyright
Other

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