Numerical Investigation of Active Flow Control using DBD Plasma Actuator on a NACA۶۴۱۲ Airfoil

Active flow control techniques, such as Dielectric Barrier Discharge (DBD) plasma actuators, have gained significant attention in modern aerodynamics for their ability to enhance aerodynamic performance by delaying flow separation, reducing drag, and improving lift characteristics. This study investigates the effect of plasma actuator placement on a NACA۶۴۱۲ airfoil at a ۱۰-degree angle of attack using Computational Fluid Dynamics (CFD). The results demonstrate that actuator placement significantly influences the effectiveness of momentum injection into the boundary layer. Actuators positioned closer to the leading edge (۳% and ۱۰% chord) are able to induce stronger jets under the influence of favorable pressure gradients and thinner boundary layers, effectively delaying separation at lower velocities. Actuators placed near the trailing edge (۴۰% and ۶۵% chord) demonstrate different performance according to the incoming flow velocity, with the ۶۵% location being more effective at higher velocities. Also, the aerodynamic performance factors of C₁ and Ca are analyzed and the ۳% configuration shown the best performance in controlling drag and increasing lift simultaneously. This study highlights the importance of actuator placement and flow conditions in optimizing plasma-based flow control strategies for improved aerodynamic performance.

کلیدواژه ها:

Flow Control ، DBD Plasma Actuator ، Separation Control ، Momentum Injection ، Naca۶۴۱۲