抄録
This study deals with the separation control on airfoil when a dielectric barrier discharge (DBD) plasma actuator is mounted on the leading edge. The experiments are performed at Re = 67,000 in an external airflow of 10 m/s. DBD plasma actuator is installed at x/c = 0.025 of 100 mm chord and 150 mm width of NACA0015 airfoil model. Flow visualization, lift force and velocity measurements are conducted for on and off modes of the actuator (pulse modulated drive). As a result, pulse modulation condition is able to delay stall up to α = 17° comparing with α = 15° for 100% duty ratio condition. In term of non-dimensional pulse modulation frequency St, it is concluded that maximum lift coefficient CL is obtained when St = 4.0, while CL becomes lower when St = 0.6. With an increase in α, CL decreases sharply after the maximum point and this is entirely different from the case of St = 0.6, where the values of CL are reduced gradually. In the case of high angle of attack (α = 18°) which angle of attack exceeds the maximum CL, the results suggest that there exists optimum pulse length for effective flow control.
