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An implicit algorithm for the conservative transonic full potential equation using an arbitrary meshA new, implicit approximate factorization (AF) algorithm designed to solve the conservative full-potential equation for the transonic flow past arbitrary airfoils has been developed. The new algorithm uses an upwind bias of the density coefficient to provide stability in supersonic regions. This allows the simple two- and three-banded matrix form of the AF scheme to be retained over the entire flow field, even in regions of supersonic flow. A numerical transformation is used to establish an arbitrary body-fitted finite-difference mesh. Airfoil pressure distributions have been computed and are in good agreement with independent results.
Document ID
19780057917
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Holst, T. L.
(NASA Ames Research Center Moffett Field, Calif., United States)
Date Acquired
August 9, 2013
Publication Date
July 1, 1978
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 78-1113
Meeting Information
Meeting: Fluid and Plasma Dynamics Conference
Location: Seattle, WA
Start Date: July 10, 1978
End Date: July 12, 1978
Sponsors: American Institute of Aeronautics and Astronautics
Accession Number
78A41826
Distribution Limits
Public
Copyright
Other

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