![]() At these high Re, a wall-modeled LES (WMLES) approach is thus required. To be pertinent for large wind turbines, the simulations would need to be at low Mach numbers (M ≤ 0.3) where compressible approaches are often limited and at large Reynolds numbers (Re ≥ 106) where wall-resolved LES is still unaffordable. The present study aims at evaluating this methodology on an application which is relevant for that sector and focuses on blade section aerodynamics characterization. It is however not used in the wind energy sector yet. The DG method has shown high accuracy, excellent scalability and capacity to handle unstructured meshes. The present work is hence considered as a strong step forward in the use of LES at high Reynolds numbers.Ībstract = "This paper aims at evaluating the potential of the Discontinuous Galerkin (DG) methodology for Large-Eddy Simulation (LES) of wind turbine airfoils. In this case, although the wall model approach used for the WMLES is very basic and not supposed to handle separation nor adverse pressure gradients, all three methods provide equivalent accuracy on averaged quantities. At high Reynolds number (Re = 1.64 × 106), the NACA4412 airfoil is studied close to stall condition. The LES results agree slightly better with the experimental chordwise pressure distribution than both XFOIL and RANS results. At low Reynolds number (Re = 6 × 104), involving laminar boundary layer separation and transition in the detached shear layer, the Eppler 387 airfoil is studied at two angles of attack. In order to first validate the LES methodology, before the WMLES approach, this study presents airfoil flow simulations at low and high Reynolds numbers and compares the results to state-of-the-art models used in industry, namely the panel method (XFOIL with boundary layer modeling) and Reynolds Averaged Navier-Stokes (RANS). ![]() This paper aims at evaluating the potential of the Discontinuous Galerkin (DG) methodology for Large-Eddy Simulation (LES) of wind turbine airfoils.
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