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Improved method for solving the viscous shock layer equationsAn improved method for solving the viscous shock layer equations for supersonic/hypersonic flows past blunt-nosed bodies is presented. The method is capable of handling slender to thick bodies. The solution is obtained by solving a coupled set of five equations, built of the four basic viscous shock layer equations and an additional equation for the standoff distance. The coupling of the equations prevents the local iterations divergence problems encountered by previous methods of solution far downstream on slender bodies. It also eliminates the need for local iterations, which were required by previous methods of solution, for a first-order scheme in the streamwise direction. A new global iteration procedure is employed to impose the shock boundary conditions. The procedure prevents the global iteration instability encountered by the basic method of solution and improves the convergence rate of the global iteration procedure of later methods devised to overcome this difficulty. The new technique reduces the computation time by 65-95 percent as compared to previous methods of solution. The method can efficiently be implemented in vector/parallel computers.
Document ID
19920063214
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Gordon, Rachel
(Texas A & M University College Station, United States)
Davis, R. T.
(Cincinnati, University OH, United States)
Date Acquired
August 15, 2013
Publication Date
July 1, 1992
Publication Information
Publication: AIAA Journal
Volume: 30
Issue: 7 Ju
ISSN: 0001-1452
Subject Category
Fluid Mechanics And Heat Transfer
Accession Number
92A45838
Funding Number(s)
CONTRACT_GRANT: NAG1-548
Distribution Limits
Public
Copyright
Other

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