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Titolo:
Flow computations around delta wings using unstructured hybrid grids
Autore:
Kano, S; Nakahashi, K;
Indirizzi:
Tohoku Univ, Dept Aeronaut & Space Engn, Sendai, Miyagi 980857901, Japan Tohoku Univ Sendai Miyagi Japan 980857901 Sendai, Miyagi 980857901, Japan
Titolo Testata:
JOURNAL OF AIRCRAFT
fascicolo: 2, volume: 36, anno: 1999,
pagine: 374 - 379
SICI:
0021-8669(199903/04)36:2<374:FCADWU>2.0.ZU;2-5
Fonte:
ISI
Lingua:
ENG
Soggetto:
IMPLICIT SCHEMES; VORTICAL FLOWS; REFINEMENT;
Tipo documento:
Article
Natura:
Periodico
Settore Disciplinare:
Engineering, Computing & Technology
Citazioni:
30
Recensione:
Indirizzi per estratti:
Indirizzo: Kano, S Tohoku Univ, Dept Aeronaut & Space Engn, Sendai, Miyagi 980857901,Japan Tohoku Univ Sendai Miyagi Japan 980857901 Miyagi 980857901, Japan
Citazione:
S. Kano e K. Nakahashi, "Flow computations around delta wings using unstructured hybrid grids", J AIRCRAFT, 36(2), 1999, pp. 374-379

Abstract

The capability of an unstructured hybrid grid method to compute the compressible Navier-Stokes equations is discussed for vortical flows over slenderdelta wings at low subsonic, high-alpha conditions as a basic study of off-design aerodynamics of high speed civil transport configurations. Computations of these nons require high resolutions of the boundary layers on the wing and of the vortical flow region above the wing. The unstructured hybridgrid, which is composed of a prismatic grid in boundary layers and tetrahedral and pyramidal grids for the remaining region, is used to treat such viscous hows, The compressible Navier-Stokes equations are solved on the hybrid grid by a cell-vertex, upwind finite volume method. The lower-upper-symmetric Gauss-Seidel implicit time integration scheme Is used for the convergence acceleration to steady state, The numerical accuracy of the present method is discussed by comparing with the experimental data for the same configurations. It is demonstrated that the present hybrid grid method is efficient and accurate enough to predict the vortical flow fields over the deltawings.

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Documento generato il 28/09/20 alle ore 12:13:35