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Algebraic grid generation for wing-fuselage bodiesAn algebraic procedure for the generation of boundary-fitted grids about wing-fuselage configurations is presented. A wing-fuselage configuration is specified by cross sections and mathematically represented by Coons' patches. A configuration is divided into sections so that several grid blocks that either adjoin each other or partially overlap each other can be generated, and each grid has six surfaces that map into a computational cube. Grids are first determined on the six boundary surfaces and then in the interior. Grid curves that are on the surface of the configuration are derived using plane-patch intersections, and single-valued functions relating approximate arc lengths along the curves to computational coordinates define the distribution of grid points. The two-boundary technique and transfinite interpolation are used to determine the boundary surface grids that are not on the configuration, and transfinite interpolation with linear blending functions is used to determine the interior grids.
Document ID
19840035039
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Smith, R. E.
(NASA Langley Research Center Hampton, VA, United States)
Everton, E. L.
(NASA Langley Research Center Hampton, VA, United States)
Kudlinski, R. A.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 12, 2013
Publication Date
January 1, 1984
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 84-0002
Accession Number
84A17826
Distribution Limits
Public
Copyright
Other

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