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Application of the TRANAIR rectangular grid approach to the aerodynamic analysis of complex configurationsA numerical method is described which uses a rectangular grid to solve the nonlinear full potential equation about complex configurations. The grid is locally refined to resolve high velocity gradients arising from leading edge expansions or shock waves. The grid penetrates the boundary (described by networks of quadrilateral panels) and is generated automatically. Discrete operators are constructed using the finite element method. The system of nonlinear discrete equations is solved iteratively using a Krylov subspace method preconditioned by an exterior Poisson solver and a direct sparse solver. The primary emphasis is to provide design engineers with an aerodynamic analysis tool (the TRANAIR code) which is accurate, reliable, economical, and flexible to use. Computational results for many interesting configurations are presented.
Document ID
19900012680
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Johnson, Forrester T.
(Boeing Commercial Airplane Co. Seattle, WA., United States)
Samant, Satish S.
(Boeing Commercial Airplane Co. Seattle, WA., United States)
Bieterman, Michael B.
(Boeing Commercial Airplane Co. Seattle, WA., United States)
Melvin, Robin G.
(Boeing Commercial Airplane Co. Seattle, WA., United States)
Young, David P.
(Boeing Commercial Airplane Co. Seattle, WA., United States)
Bussoletti, John E.
(Boeing Advanced Systems Co. Seattle, WA., United States)
Madson, Mike D.
(NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
August 14, 2013
Publication Date
March 1, 1990
Publication Information
Publication: AGARD, Applications of Mesh Generation to Complex 3-D Configurations
Subject Category
Aerodynamics
Accession Number
90N21996
Funding Number(s)
CONTRACT_GRANT: NAS2-12513
Distribution Limits
Public
Copyright
Other
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