Active flow control of high-angle of attack aeroacoustics noise; computational studies using LES

Flow separation has been a challenging issue for both rotary and fixed wing aerodynamics. In the present research we propose an active flow control technique using synthetic jets, for fixed wing at high angle of attack. The studies are carried out for NACA4412, for angles of attack AoA=12⁰, 15⁰ and 18⁰. The study concern the impact of the speed of the impinging jet and angle of injection on the flow separation and acoustics noise. The air is injected in a region close to the leading-edge. The computational studies are carried out using the large-eddy simulation (LES) approach. The studies shows that the active flow control technique using the synthetic jets is an efficient approach for the control of flow separation. The study shows that both the jet injection angle and blowing ratio affect the flow separation and contribute significantly to the reduction of the flow separation and implicitly to the acoustics noise.