| DOI | Trouver le DOI : https://doi.org/10.2514/6.2011-2139 |
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| Auteur | Rechercher : Wang, B.; Rechercher : Poirel, D.; Rechercher : Yuan, W.1; Rechercher : Zha, G.-C. |
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| Affiliation | - Conseil national de recherches du Canada. Aérospatiale
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| Format | Texte, Article |
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| Conférence | 52nd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference, 4 April 2011 through 7 April 2011, Denver, CO |
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| Sujet | Central differencing schemes; Compressible Navier-Stokes equations; Computer clusters; Differencing scheme; Dual time stepping method; Fully-coupled; Gauss-Seidel relaxation; High-order scheme; Initial solution; Inviscid fluxes; Low-amplitude; Message passing interface; Parallel Computation; Pitching motion; Preconditioning method; Self-sustained oscillations; Small amplitude; Structure dynamics; Subgrid scale models; Temporal terms; Time marching; Weighted essentially nonoscillatory scheme; Airfoils; Computational fluid dynamics; Computer simulation; Experiments; Message passing; Navier Stokes equations; Reynolds number; Structural dynamics; Iterative methods |
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| Résumé | This paper is to investigate self-sustained oscillations of a NACA 0012 airfoil at a transitional Reynolds number using large-eddy simulation (LES). The unsteady compressible Navier-Stokes equations coupled with the Smagorinsky sub-grid scale (SGS) model are solved using a dual time stepping method. The unfactored line Gauss-Seidel relaxation iteration is employed for time marching. The physical temporal terms are discretized using a 2nd-order accuracy backward differencing scheme. To achieve high accuracy, a 5th-order weighted essentially non-oscillatory (WENO) scheme is used for the inviscid fluxes. The viscous terms are discretized using a fully conservative 4th-order or 2nd-order central differencing scheme. A preconditioning method is used for the unsteady computations of the static airfoil at the beginning to generate a good initial solution for the fluid-structural interaction (FSI) computations. A fully coupled fluid-structural methodology is employed. The structurally linear one-degree-of-freedom equation of pitching motion is solved according to the low-amplitude self-sustained oscillations observed in the experiment. All simulations are conducted on a message-passing interface (MPI)-based computer cluster with parallel computations to reduce the wall clock time. The preliminary two-dimensional (2D) LES results show that the developed computational fluid dynamics (CFD)/computational structure dynamics (CSD) simulation is able to capture the self-sustained oscillations with small amplitudes observed in the experiment. Copyright © 2011 by the American Institute of Aeronautics and Astronautics, Inc. |
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| Date de publication | 2011 |
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| Dans | |
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| Langue | anglais |
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| Publications évaluées par des pairs | Oui |
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| Numéro NPARC | 21271482 |
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| Exporter la notice | Exporter en format RIS |
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| Signaler une correction | Signaler une correction (s'ouvre dans un nouvel onglet) |
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| Identificateur de l’enregistrement | 8ab3cf7e-6fb1-400b-a965-599232b9d052 |
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| Enregistrement créé | 2014-03-24 |
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| Enregistrement modifié | 2020-04-21 |
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