Multigrid technique for the compressible Euler and Navier-Stokes equations

Kanarachos, AE; Vournas, IP

dc.contributor.author	Kanarachos, AE	en
dc.contributor.author	Vournas, IP	en
dc.date.accessioned	2014-03-01T01:09:28Z
dc.date.available	2014-03-01T01:09:28Z
dc.date.issued	1993	en
dc.identifier.issn	02644401	en
dc.identifier.uri	https://dspace.lib.ntua.gr/xmlui/handle/123456789/11008
dc.subject	navier-stokes equation	en
dc.subject.other	Aerodynamics	en
dc.subject.other	Airfoils	en
dc.subject.other	Codes (symbols)	en
dc.subject.other	Eigenvalues and eigenfunctions	en
dc.subject.other	Finite element method	en
dc.subject.other	Laminar flow	en
dc.subject.other	Mathematical models	en
dc.subject.other	Optimization	en
dc.subject.other	Turbulent flow	en
dc.subject.other	Viscous flow	en
dc.subject.other	Messerschmitt Bolkow Blohm GmbH (MBB)	en
dc.subject.other	Multigrid techniques	en
dc.subject.other	Navier Stokes solver using characteristic flux extrapolation	en
dc.subject.other	NSFLEX-code	en
dc.subject.other	Compressible flow	en
dc.title	Multigrid technique for the compressible Euler and Navier-Stokes equations	en
heal.type	journalArticle	en
heal.identifier.primary	10.1108/eb023898	en
heal.identifier.secondary	http://dx.doi.org/10.1108/eb023898	en
heal.publicationDate	1993	en
heal.abstract	An optimized multigrid method (NSFLEX-MG) for the NSFLEX-code (Navier-Stokes solver using characteristic flux extrapolation) of MBB (Messerschmitt Bolkow Blohm GmbH) is described. The method is based on a correction scheme and implicit relaxation procedures and is applied to two-dimensional test cases. The principal feature of the flow solver is a Godunov-type averaging procedure based on the eigenvalues analysis of the Euler equations by means of which the inviscid fluxes are evaluated at the finite volume faces. Viscous fluxes are centrally differenced at each cell face. The performance of NSFLEX-MG is demonstrated for a large range of Mach numbers for compressible inviscid and viscous (laminar and turbulent) flows over a RAE-2822 airfoil and over a NACA-0012 airfoil.	en
heal.journalName	Engineering computations	en
dc.identifier.doi	10.1108/eb023898	en
dc.identifier.volume	10	en
dc.identifier.issue	2	en
dc.identifier.spage	123	en
dc.identifier.epage	137	en