ON THE ACCURACY AND EFFICIENCY OF CFD METHODS IN REAL-GAS HYPERSONICS

DRIKAKIS, D; TSANGARIS, S

dc.contributor.author	DRIKAKIS, D	en
dc.contributor.author	TSANGARIS, S	en
dc.date.accessioned	2014-03-01T01:09:29Z
dc.date.available	2014-03-01T01:09:29Z
dc.date.issued	1993	en
dc.identifier.issn	0271-2091	en
dc.identifier.uri	https://dspace.lib.ntua.gr/xmlui/handle/123456789/11015
dc.subject	EULER NAVIER-STOKES EQUATIONS	en
dc.subject	HYPERSONIC FLOWS	en
dc.subject	REAL GAS	en
dc.subject	UPWIND SCHEME	en
dc.subject.classification	Computer Science, Interdisciplinary Applications	en
dc.subject.classification	Mathematics, Interdisciplinary Applications	en
dc.subject.classification	Mechanics	en
dc.subject.classification	Physics, Fluids & Plasmas	en
dc.subject.other	FLUX-SPLIT ALGORITHMS	en
dc.subject.other	EULER EQUATIONS	en
dc.title	ON THE ACCURACY AND EFFICIENCY OF CFD METHODS IN REAL-GAS HYPERSONICS	en
heal.type	journalArticle	en
heal.identifier.primary	10.1002/fld.1650160902	en
heal.identifier.secondary	http://dx.doi.org/10.1002/fld.1650160902	en
heal.language	English	en
heal.publicationDate	1993	en
heal.abstract	A study of viscous and inviscid hypersonic flows using generalized upwind methods is presented. A new family of hybrid flux-splitting methods is examined for hypersonic flows. The hybrid method is constructed by the superposition of the flux-vector-splitting (FVS) method and second-order artificial dissipation in the regions of strong shock waves. The conservative variables on the cell faces are calculated by an upwind extrapolation scheme to third-order accuracy. A second-order-accurate scheme is used for the discretization of the viscous terms. The solution of the system of equations is achieved by an implicit unfactored method. In order to reduce the computational time, a local adaptive mesh solution (LAMS) method is proposed. The LAMS method combines the mesh-sequencing technique and local solution of the equations. The local solution of either the Euler or the Navier Stokes equations is applied for the region of the flow field where numerical disturbances die out slowly. Validation of the Euler and Navier-Stokes codes is obtained for hypersonic flows around blunt bodies. Real gas effects are introduced via a generalized equation of state.	en
heal.publisher	JOHN WILEY & SONS LTD	en
heal.journalName	INTERNATIONAL JOURNAL FOR NUMERICAL METHODS IN FLUIDS	en
dc.identifier.doi	10.1002/fld.1650160902	en
dc.identifier.isi	ISI:A1993LA75500001	en
dc.identifier.volume	16	en
dc.identifier.issue	9	en
dc.identifier.spage	759	en
dc.identifier.epage	775	en