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Design of supercritical swept wingsComputational fluid dynamics are used to discuss problems inherent to transonic three-dimensional flow past supercritical swept wings. The formulation for a boundary value problem for the flow past the wing is provided, including consideration of weak shock waves and the use of parabolic coordinates. A swept wing code is developed which requires a mesh of 152 x 10 x 12 points and 200 time cycles. A formula for wave drag is calculated, based on the idea that the conservation form of the momentum equation becomes an entropy inequality measuring the drag, expressible in terms of a small-disturbance equation for a potential function in two dimensions. The entropy inequality has been incorporated in a two-dimensional code for the analysis of transonic flow over airfoils. A method of artificial viscosity is explored for optimum pressure distributions with design, and involves a free boundary problem considering speed over only a portion of the wing.
Document ID
19820040291
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Garabedian, P.
(New York Univ. New York, NY, United States)
Mcfadden, G.
(New York University New York, NY, United States)
Date Acquired
August 10, 2013
Publication Date
March 1, 1982
Publication Information
Publication: AIAA Journal
Volume: 20
Subject Category
Aerodynamics
Accession Number
82A23826
Funding Number(s)
CONTRACT_GRANT: NGR-33-015-201
CONTRACT_GRANT: NSG-1579
Distribution Limits
Public
Copyright
Other

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