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Finite element concepts in computational aerodynamicsFinite element theory was employed to establish an implicit numerical solution algorithm for the time averaged unsteady Navier-Stokes equations. Both the multidimensional and a time-split form of the algorithm were considered, the latter of particular interest for problem specification on a regular mesh. A Newton matrix iteration procedure is outlined for solving the resultant nonlinear algebraic equation systems. Multidimensional discretization procedures are discussed with emphasis on automated generation of specific nonuniform solution grids and accounting of curved surfaces. The time-split algorithm was evaluated with regards to accuracy and convergence properties for hyperbolic equations on rectangular coordinates. An overall assessment of the viability of the finite element concept for computational aerodynamics is made.
Document ID
19780011858
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Baker, A. J.
(Tennessee Univ. Knoxville, TN, United States)
Date Acquired
August 9, 2013
Publication Date
February 1, 1978
Publication Information
Publication: NASA. Ames Res. Center Future Computer Requirements for Computational Aerodynamics
Subject Category
Computer Programming And Software
Accession Number
78N19801
Funding Number(s)
CONTRACT_GRANT: NSG-1261
CONTRACT_GRANT: NAS1-14307
CONTRACT_GRANT: NSG-1391
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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