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Computation of vortex-dominated flow for a delta wing undergoing pitching oscillationThe conservative, unsteady Euler equations for the flow relative to a moving frame of reference are used to solve for the three-dimensional steady and unsteady flows around a sharp-edged delta wing. The resulting equations are solved by using an implicit, approximately factored, finite-volume scheme. Implicit second-order and explicit second- and fourth-order dissipations are added to the scheme. The boundary conditions are explicitly satisfied. The grid is generated by locally using a modified Joukowski transformation in crossflow planes at the grid-chord stations. The computational applications cover a steady flow around a delta wing, whose results serve as the initial conditions for the unsteady flow around a pitching delta wing at a large mean angle of attack. The steady results are compared with the experimental data, and the unsteady results are compared with results of a flux-difference splitting scheme.
Document ID
19900062728
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Kandil, Osama A.
(Old Dominion Univ. Norfolk, VA, United States)
Chuang, H. Andrew
(Old Dominion University Norfolk, VA, United States)
Date Acquired
August 14, 2013
Publication Date
September 1, 1990
Publication Information
Publication: AIAA Journal
Volume: 28
ISSN: 0001-1452
Subject Category
Aerodynamics
Accession Number
90A49783
Funding Number(s)
CONTRACT_GRANT: NAG1-648
CONTRACT_GRANT: NAG1-846
Distribution Limits
Public
Copyright
Other

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