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Grid generation about complex three-dimensional aircraft configurationsThe problem of obtaining three dimensional grids with sufficient resolution to resolve all the flow or other physical features of interest is addressed. The generation of a computational grid involves a series of compromises to resolve several conflicting requirements. On one hand, one would like the grid to be fine enough and not too skewed to reduce the numerical errors and to adequately resolve the pertinent physical features of the flow field about the aircraft. On the other hand, the capabilities of present or even future supercomputers are finite and the number of mesh points must be limited to a reasonable number: one which is usually much less than desired for numerical accuracy. One technique to overcome this limitation is the 'zonal' grid approach. In this method, the overall field is subdivided into smaller zones or blocks in each of which an independent grid is generated with enough grid density to resolve the flow features in that zone. The zonal boundaries or interfaces require special boundary conditions such that the conservation properties of the governing equations are observed. Much work was done in 3-D zonal approaches with nonconservative zonal interfaces. A 3-D zonal conservative interfacing method that is efficient and easy to implement was developed during the past year. During the course of the work, it became apparent that it would be much more feasible to do the conservative interfacing with cell-centered finite volume codes instead of the originally planned finite difference codes. Accordingly, the CNS code was converted to finite volume form. This new version of the code is named CNSFV. The original multi-zonal interfacing capability of the CNS code was enhanced by generalizing the procedure to allow for completely arbitrarily shaped zones with no mesh continuity between the zones. While this zoning capability works well for most flow situations, it is, however, still nonconservative. The conservative interface algorithm was also implemented but was not completely validated.
Document ID
19910012758
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Klopfer, Goetz H.
(MCAT Inst. San Jose, CA, United States)
Date Acquired
September 6, 2013
Publication Date
April 1, 1991
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.26:188097
NASA-CR-188097
MCAT-91-003
Report Number: NAS 1.26:188097
Report Number: NASA-CR-188097
Report Number: MCAT-91-003
Accession Number
91N22071
Funding Number(s)
CONTRACT_GRANT: NCC2-616
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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