Abstract
The flow around thick and symmetric NACA0021 airfoil at angle of attack 60°, is studied at the Reynolds number based on the chord length \(Re = \frac{{U_\infty C}}{\nu } = 2.7 \times 10^5 \). Hybrid Detached Eddy Simulation (DES) approaches are used, with improvement by means of Organised Eddy Simulation (OES) in the context of the URANS part.
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Acknowledgments
This work has been carried out in the research group EMT2 (Ecoulements Mono-phasiques, Transitionnels et Turbulents) of the Institut de Mécanique des Fluides de Toulouse. Part of this work is carried out on the basis of CPU allocations of the national computer centres of France CINES, CALMIP and IDRIS. This study is part of the European program DESIDER, N AST3-CT-2003-502842, coordinated by EADS.
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El Akoury, R., Braza, M., Hoarau, Y., Vos, J., Harran, G., Sevrain, A. (2009). Unsteady Flow Around a NACA0021 Airfoil Beyond Stall at 60° Angle of Attack. In: Braza, M., Hourigan, K. (eds) IUTAM Symposium on Unsteady Separated Flows and their Control. IUTAM Bookseries, vol 14. Springer, Dordrecht. https://doi.org/10.1007/978-1-4020-9898-7_35
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DOI: https://doi.org/10.1007/978-1-4020-9898-7_35
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