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Computation of transonic vortex flows past delta wings Integral equation approachThe steady full-potential equation is written in the form of Poisson's equation, and the solution of the velocity field is expressed in terms of an integral equation. The solution consists of a surface integral of vorticity distribution on the wing and its free-vortex sheets and a volume integral of source distribution within a volume around the wing and its free-vortex sheets. The solution is obtained through successive iteration cycles. The source distribution is computed by using a mixed finite-difference scheme of the Murman-Cole type. The method is applied to delta wings. Numerical examples show that a conical shock is captured on the suction side of the wing. It is attached to the lower surface of the leading-edge vortex but does not necessarily reach to the wing surface.
Document ID
19850059264
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Kandil, O. A.
(Old Dominion University Norfolk, VA, United States)
Yates, E. C., Jr.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 12, 2013
Publication Date
July 1, 1985
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 85-1582
Accession Number
85A41415
Funding Number(s)
CONTRACT_GRANT: NAG1-591
Distribution Limits
Public
Copyright
Other

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