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Algebraic grid generation about wing-fuselage bodiesAn algebraic procedure for generating boundary-fitted grids about wing-fuselage configurations is presented. A wing-fuselage configuration consists of two aircraft components specified by cross sections and mathematically represented by Coons' patches. Several grid blocks are constructed to cover the entire region surrounding the configuration, and each grid block maps into a computational cube. Grid points are first determined on the six boundary surfaces of a block and then in the interior. Grid points on the surface of the configuration are derived from the intersection of planes with the Coons' patch definition. Approximate arc length distributions along the resulting grid curves concentrate and disperse grid points. The two-boundary technique and transfinite interpolation are used to determine grid points on the remaining boundary surfaces and block interiors.
Document ID
19880036896
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Smith, R.E.
(NASA Langley Research Center Hampton, VA, United States)
Kudlinski, R. A.
(NASA Langley Research Center Hampton, VA, United States)
Everton, E. L.
(NASA Langley Research Center Hampton, VA, United States)
Wiese, M. R.
(Computer Sciences Corp. Hampton, VA, United States)
Date Acquired
August 13, 2013
Publication Date
December 1, 1987
Publication Information
Publication: Journal of Aircraft
Volume: 24
ISSN: 0021-8669
Subject Category
Aerodynamics
Accession Number
88A24123
Distribution Limits
Public
Copyright
Other

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