Experimental Study on Flow Control of Low-speed Delta Wing Using Nanosecond Pulsed Plasma Actuator

Force measurement in low-speed wind tunnel is conducted to improve the aerodynamics of 47deg delta wing using nanosecond pulse dielectric barrier discharge plasma actuator at the free-stream flow velocity of 30m/s. In order to investigate the optimized flow control effects, we design five different plasma actuator arrangements under five different positions and get the lift and drag coefficient of each plasma actuators. The results show that the position of plasma actuator determines flow control effect greatly and that leading edge plasma actuator can significantly improve the aerodynamics of delta wing and delay stall angle, while plasma actuator erected at different span-wise position on the upper surface can not affect the aerodynamics of delta wing. It is also found that flow control effect also depends on frequency. When the peak-peak voltage is 13kV, we find the flow control effect of 200Hz is the best, which increases lift coefficient at angle 30deg from 1.31 to 1.44 by 9.6%, lift-drag ratio by 3.3%.