Experimental Investigation of effect Slotted leading Edge Circulation Control Aerofoil Aerodynamic and Acoustics

This study discusses the separation flow active flow control of the NACA 633618-il three-dimensional straight aerofoil, which is carried out by using the inclined exit synthetic jet exciter. The synthetic jet can effectively control the flow separation of the wings, increase the maximum lift coefficient by 12.4%, and delay the stall angle of attack by 6°. Using boundary layer testing techniques and The particle image velocimetry system is used to study and analyse the control mechanism of the synthetic jet separation flow. The results show that the boundary layer velocity pattern becomes full after the control. The shape factor decreases, the underlying energy increases, and the ability to resist adverse pressure gradients increases. The transient and real-time homogenised PIV test flow field map further proves the synthetic jet flow direction. After the main flow is injected and mixed with momentum, the main flow adheres to the aerofoil surface, the fluid turbulent kinetic energy and Reynolds shear stress near the aerofoil increase, and the separation point is pushed downstream. Later, flow separation is inhibited.