![]() thesis, Ecole polytechnique de Louvain/iMMC (2013)Ĭarton de Wiart, C., Hillewaert, K., Duponcheel, M., Winckelmans, G.: Assessment of a discontinuous Galerkin method for the simulation of vortical flows at high Reynolds number. Hillewaert, K.: Development of the Discontinuous Galerkin Method for High-Resolution, Large Scale CFD and Acoustics in Industrial Geometries. 34(6), 1111–1119 (1996)ĭuprat, C., Balarac, G., Métais, O., Congedo, P.M., Brugière, O.: A wall-layer model for large-eddy simulations of turbulent flows with/out pressure gradient. TM-1999-209398, National Aeronautics and Space Administration Glenn Research Center (1999)īalaras, E., Benocci, C., Piomelli, U.: Two-layer approximate boundary conditions for large-eddy simulations. Shih, T.H., Povinelli, L.A., Liu, N.S., Potapczuk, M.G., Lumley, J.L.: A generalized wall function. 155–168 (1993)īrionnaud, R., Holmann, D.M., Modena, M.C.: Aerodynamic analysis of the 2nd AIAA High Lift Prediction Workshop by a Lattice-Boltzmann Method solver (2014) Werner, H., Wengle, H.: Large-Eddy Simulation of Turbulent Flow over and around a Cube in a Plate Channel. Series in Mechanical Engineering, McGraw-Hill (1979)ĪNSYS Fluent Theory Guide: 4.14.9 LES Near-Wall Treatment. Schlichting, H.: Boundary Layer Theory, 7th edn. Marquillies, M., Laval, J.P., Dolganov, R.: Direct numerical simulation of a separated channel flow with a smooth profile. TurbBase Cineca IRODS repository, data creator: Laval, J.-P.īernard, A., Foucaut, J., Dupont, P., Stanislas, M.: Decelerating boundary layer: a new scaling and mixing length model. 1223 (2017)ĭirect Numerical Simulations of channel flow over a smooth geometry (Dataset: “DNS channel flow with APG”). In: 55th AIAA Aerospace Sciences Meeting, pp. Fluids 26(1), 015108 (2014)Ĭarton de Wiart, C., Murman, S.M.: Assessment of wall-modeled LES strategies within a discontinuous-Galerkin spectral-element framework. Park, G.I., Moin, P.: An improved dynamic non-equilibrium wall-model for large eddy simulation. Journal of Physics: Conference Series 753(022037). Fluids 26(1), 015104 (2014)įrère, A., Sørensen, N.N., Hillewaert, K., Chatelain, P., Winckelmans, G.: Discontinuous galerkin methodology for large-eddy simulations of wind turbine airfoils. Springer, Netherlands (2010)īose, S., Moin, P.: A dynamic slip boundary condition for wall-modeled large-eddy simulation. Piomelli, U.: Wall-Modeled Large-Eddy Simulations: Present Status and Prospects. Larsson, J., Kawai, S., Bodart, J., Bermejo-Moreno, I.: Large eddy simulation with modeled wall-stress: recent progress and future directions. Kawai, S., Larsson, J.: Wall-modeling in large eddy simulation: length scales, grid resolution, and accuracy. Fluids 36(5), 817–837 (2007)Ĭabot, W., Moin, P.: Approximate wall boundary conditions in the Large-Eddy simulation of high Reynolds number flow. Therefore, it is argued that if the convective terms are neglected, the pressure-gradient term needs to be neglected as well.īreuer, M., Kniazev, B., Abel, M.: Development of wall models for LES of separated flows using statistical evaluations. ![]() This simplification applied to the TLM indeed leads to a higher error than the simple equilibrium models. The study reveals also that the often used simplification of the “Two-Layer Model”(TLM) that takes the pressure-gradient into account but neglects the convective terms, is not adequate. It appears that the simple models, which assume an equilibrium flow, provide a better match to the mean flow velocity than allegedly more advanced models. In order to aid wall-model development, the second part of the paper characterizes the effect of the adverse pressure-gradient (APG) on the turbulent boundary layer development, and evaluates different wall-models in an a priori manner. In the first part of the paper, the results are compared to previous experimental and numerical results, showing close agreement with both. The flow around the NACA4412 airfoil, a widely used test case for turbulence modeling validation, is computed at Reynolds number R e = 1.64 × 10 6 and angle of attack α = 12 ∘. This paper presents an in-depth study, using wall-resolved Large-Eddy Simulation (wrLES), of a high Reynolds number airfoil in a near-stall condition.
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