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Component-adaptive grid embeddingOne of the major problems related to transonic flow prediction about realistic aircraft configuration is the generation of a suitable grid which encompasses such configurations. In general, each aircraft component (wing, fuselage, nacelle) requires a grid system that is usually incompatible with the grid systems of the other components; thus, the implementation of finite-difference methods for such geometrically-complex configurations is a difficult task. An approach was developed to treat such a problem. The basic idea is to generate different grid systems, each suited for a particular component. Thus, the flow field domain is divided into overlapping subdomains of different topology. These grid systems are then interfaced with each other in such a way that stability, convergence speed and accuracy are maintained.
Document ID
19810006183
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Atta, E. H.
(Lockheed-Georgia Co. Marietta, GA, United States)
Date Acquired
August 11, 2013
Publication Date
January 1, 1980
Publication Information
Publication: NASA. Langley Research Center Numerical Grid Generation Tech.
Subject Category
Numerical Analysis
Accession Number
81N14697
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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