This study investigates the effect of a DBD plasma actuator installed at the leading edge of a NACA0012 airfoil under low Reynolds number conditions. Wind tunnel experiments were conducted at a flow speed of 5 m/s, measuring surface pressure distributions at angles of attack from 0° to 18°. The results revealed that the actuator increased lift by enhancing negative pressure on the upper surface, especially near stall. The effect varied between pre-stall and post-stall regimes, indicating changes in flow behavior. Even at α = 18°, the actuator showed partial effectiveness in flow control. Flow visualization is planned to clarify the underlying mechanism.
Norimoto et al. (Wed,) studied this question.