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Numerical flux formulas for the Euler and Navier-Stokes equations. 2: Progress in flux-vector splittingThe accuracy of various numerical flux functions for the inviscid fluxes when used for Navier-Stokes computations is studied. The flux functions are benchmarked for solutions of the viscous, hypersonic flow past a 10 degree cone at zero angle of attack using first order, upwind spatial differencing. The Harten-Lax/Roe flux is found to give a good boundary layer representation, although its robustness is an issue. Some hybrid flux formulas, where the concepts of flux-vector and flux-difference splitting are combined, are shown to give unsatisfactory pressure distributions; there is still room for improvement. Investigations of low diffusion, pure flux-vector splittings indicate that a pure flux-vector splitting can be developed that eliminates spurious diffusion across the boundary layer. The resulting first-order scheme is marginally stable and not monotone.
Document ID
19910012771
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Coirier, William J.
(NASA Lewis Research Center Cleveland, OH., United States)
Vanleer, Bram
(Michigan Univ. Ann Arbor., United States)
Date Acquired
September 6, 2013
Publication Date
January 1, 1991
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-104353
E-6138
AIAA PAPER 91-1566
NAS 1.15:104353
Report Number: NASA-TM-104353
Report Number: E-6138
Report Number: AIAA PAPER 91-1566
Report Number: NAS 1.15:104353
Meeting Information
Meeting: Computational Fluid Dynamics Conference
Location: Honolulu, HI
Country: United States
Start Date: June 24, 1991
End Date: June 27, 1991
Sponsors: AIAA
Accession Number
91N22084
Funding Number(s)
PROJECT: RTOP 505-62-52
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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