Large-eddy simulations were carried out to describe the flow past a high-lift wing section. The configuration consists of a baseline laminar flow geometry, with smoothly deflected leading and trailing-edge flaps, corresponding to a wind tunnel model. Both flaps are deployed at a 45 deg angle with respect to the undeflected state, and blowing from internal plenums is employed to mitigate transition, increase attached flow, and enhance lift. Solutions were obtained to the Navier-Stokes equations, at the experimental chord-based Reynolds number of 1 × 10~6 and Mach number of 0.14. The numerical method is based upon a high-fidelity scheme and an implicit time-marching approach. Results were generated for two different angles of attack, in freestream conditions and within the confines of wind tunnel walls. Comparisons are made with available experimental data in terms of surface pressure distributions, and the effect of blowing is quantified by comparison to baseline cases without control. Details of the computations are described, and physical features of the computed flowfields are characterized.
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