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Sixth International Symposium on Turbulence and Shear Flow Phenomena
June, 22-24, 2009 , Seoul National University, Seoul, Korea

DOI: 10.1615/TSFP6

HYBRID RANS-LES MODELLING OF TURBULENT FLOW AROUND A THREE-ELEMENT AIRFOIL

pages 529-534
DOI: 10.1615/TSFP6.840
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RÉSUMÉ

An algebraic hybrid RANS-LES (HYB0) model was applied to the A310 high-lift three-element configuration at a freestream Mach number of M = 0.22. Computations were conducted for two different angles of attack at α = 12.2° and α = 25.2°, respectively, with or without prescribed transition around the leading edges of the slat, main wing and flap. At α = 25.2°, wind tunnel test indicated a stalled flow with a sudden drop in lift. The computations were compared with measured pressure distributions and, at the stall angle, with the S-A DES computation as well. It was shown that the modelling may significantly be affected by the transition specified around the leading edges, for which the eddy viscosity was switched off in the laminar boundary layer. With prescribed transition, the S-A DES model pronounced undesired boundary layer separation on the slat upper surface. For full-turbulence computations, the modelling tends to pronounce a delayed stall at a relatively large incidence. Provided that the uncertainties could be ruled out at large incidences, the modelling performance should be justifiable to scrutinize the properties of high-lift flows towards and at stall. At α = 12.2°, where the location of transition was experimentally affirmed, it was shown that hybrid modelling was able to produce reasonable predictions with appropriate grid resolution.

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