Effect of DBD Plasma Actuator Location for Boundary Layer Flow Control over NACA۰۰۱۸

This study investigates the numerical simulation of airflow around a NACA ۰۰۱۸ airfoil utilizing Dielectric Barrier Discharge (DBD) plasma actuators for active flow control. A critical factor in the efficacy of DBD-based control is the spatial positioning of the actuator along the chord. In this work, the aerodynamic performance was evaluated by placing the plasma actuator at multiple locations: x/c =۰, ۰.۱, ۰.۲ and ۰.۳. The results demonstrate that plasma actuation effectively delays flow separation, thereby significantly enhancing lift and reducing drag. Specifically, placing the actuator at x/c = ۰.۳ yielded the maximum lift enhancement and superior boundary layer control compared to the more proximal locations. These findings provide a fundamental basis for the design of intelligent, optimized flow control systems for next-generation aeronautical vehicles.

کلیدواژه ها:

Plasma actuator ، NACA۰۰۱۸ ، Actuator location ، Boundary layer