NDLI: Segmented domain decomposition multigrid for 3-d turbomachinery flows

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Segmented domain decomposition multigrid for 3-d turbomachinery flows

Content Provider	NASA Technical Reports Server (NTRS)
Author	Rubin, S. G. Celestina, M. L. Adamczyk, J. J.
Copyright Year	2001
Description	A Segmented Domain Decomposition Multigrid (SDDMG) procedure was developed for three-dimensional viscous flow problems as they apply to turbomachinery flows. The procedure divides the computational domain into a coarse mesh comprised of uniformly spaced cells. To resolve smaller length scales such as the viscous layer near a surface, segments of the coarse mesh are subdivided into a finer mesh. This is repeated until adequate resolution of the smallest relevant length scale is obtained. Multigrid is used to communicate information between the different grid levels. To test the procedure, simulation results will be presented for a compressor and turbine cascade. These simulations are intended to show the ability of the present method to generate grid independent solutions. Comparisons with data will also be presented. These comparisons will further demonstrate the usefulness of the present work for they allow an estimate of the accuracy of the flow modeling equations independent of error attributed to numerical discretization.
File Size	972354
Page Count	14
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_20020024452
Archival Resource Key	ark:/13960/t1vf1sb34
Language	English
Publisher Date	2001-01-01
Access Restriction	Open
Subject Keyword	Fluid Mechanics And Thermodynamics Flow Equations Multigrid Methods Three Dimensional Flow Segments Turbomachinery Compressors Mathematical Models Decomposition Computational Grids Grid Generation Mathematics Turbines Viscous Flow Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Article

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