Numerical simulation of self-sustained oscillations of an airfoil at a transitional reynolds number using high-order schemes

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DOIResolve DOI: http://doi.org/10.2514/6.2011-2139
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TypeArticle
Proceedings titleCollection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
Conference52nd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference, 4 April 2011 through 7 April 2011, Denver, CO
ISSN0273-4508
ISBN9781600869518
Article numberAIAA 2011-2139
SubjectCentral 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
AbstractThis 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.
Publication date
LanguageEnglish
AffiliationNational Research Council Canada (NRC-CNRC); Aerospace (AERO-AERO)
Peer reviewedYes
NPARC number21271482
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Record identifier8ab3cf7e-6fb1-400b-a965-599232b9d052
Record created2014-03-24
Record modified2016-05-09
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