Synthetic Jets Actuators (SJA) that produce a zero net mass flow rate have been locally applied at the pylon-wing junction to suppress the local flow separation caused by the closely coupled Ultra-High Bypass Ratio engine integration. The high fidelity numerical simulations utilizing unsteady Reynolds-averaged Navier-Stokes solver have been performed to simulate this problem. A wind tunnel model representing a 2.5D wing with pylon, nacelle and deployed high-lift devices has been used for this study. Active Flow Control (AFC) applied at the wing-pylon junction area can prevent larger flow separation on the wing behind the nacelle caused by the slat cutback, increase the lift and to postpone the stall angle by interaction of the vortices from the SJA with vortices dominating this region. The performed unsteady CFD simulations demonstrate the possibility to locally affect the flow separation by utilization of AFC. The geometrical setup of the actuators (number and locations) and the flow parameters (blowing coefficient, actuation frequency and phase shift) have been varied, as well. Unsteady boundary conditions were used to simulate the effect of SJA. The positive effect of the application of the SJA on the lift and local flow separation has been observed.
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