Abstract
A Large Eddy Simulation (LES) of a turbulent flow over the A-airfoil near stall at a chord Reynolds number of 2.1 × 106 is performed and compared to windtunnel experiments. This configuration still constitutes a challenging test case for Reynolds Averaged Navier-Stokes (RANS) simulation and LES due to the complexity of the suction side boundary layer: an adverse pressure gradient creates successively a laminar separation bubble, a turbulent reattachment and a separation near the trailing edge. To handle this high Reynolds number flow with LES on available supercomputers, a local mesh refinement technology and a low dissipative scheme are developed. It appears that the computed mean and fluctuating velocity profiles compare reasonably well with experimental measurements.
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