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Applications of unstructured hybrid grid method to high‐Reynolds number viscous flows
Author(s) -
Nakahashi Kazuhiro,
Sharov Dmitri,
Kano Shintaro,
Kodera Masatoshi
Publication year - 1999
Publication title -
international journal for numerical methods in fluids
Language(s) - English
Resource type - Journals
SCImago Journal Rank - 0.938
H-Index - 112
eISSN - 1097-0363
pISSN - 0271-2091
DOI - 10.1002/(sici)1097-0363(19990915)31:1<97::aid-fld957>3.0.co;2-d
Subject(s) - transonic , supersonic speed , hypersonic speed , boundary layer , mesh generation , compressible flow , computational fluid dynamics , mechanics , turbulence , reynolds number , reynolds averaged navier–stokes equations , unstructured grid , grid , geometry , compressibility , computer science , mathematics , physics , aerodynamics , finite element method , thermodynamics
In this paper, an unstructured hybrid grid method is discussed for its capability to compute three‐dimensional compressible viscous flows of complex geometry. A hybrid of prismatic and tetrahedral grids is used to accurately resolve the wall boundary layers for high‐Reynolds number viscous flows. The Navier–Stokes equations for compressible flows are solved by a finite volume, cell–vertex scheme. The LU‐SGS implicit time integration method is used to reduce the computational time for very fine grids in boundary layer regions. Two kinds of one‐equation turbulence models are evaluated here for their accuracy. The method is applied to computations of transonic flows around the ONERA M5 airplane and ONERA M6 wing, and supersonic shock/boundary layer interacting flows inside a scramjet inlet to validate the accuracy and efficiency of the method. Copyright © 1999 John Wiley & Sons, Ltd.