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In this study, the effect of the jet control width and its momentum coefficient on the flow over a NACA0012 airfoil is investigated numerically for a Reynolds number equal to 2.88x106. The jet is placed at 15% of the chord length from the leading edge on the upper surface of the airfoil. The calculation was carried out using the solver URANS with the (k-ε) RNG model. Simulation results for an incompressible fully turbulent flow, varying the jet width from 0.5 to 3.5 percent of the chord length with jet control angle β equal to 450, the lift to drag ratio increase. However, an optimum jet width of 2% of the profile chord, leads to better performance. I is also be observed, when the momentum coefficient rises, the lift coefficient increases reaching about 86% improvement (for better improvement by 85.93%) and the stall angle is delayed from 160 to 220. This parametric study led to select the control parameters for the best aerodynamic performance of the airfoil.
control, flow separation, synthetic jet, NACA0012 profile
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