Experimental investigation of aerodynamic control on a 35° swept flying wing by means of nanosecond dielectric barrier discharge （NS-DBD） plasma was carried out at subsonic flow speed of 20-40 m/s, correspondin...Experimental investigation of aerodynamic control on a 35° swept flying wing by means of nanosecond dielectric barrier discharge （NS-DBD） plasma was carried out at subsonic flow speed of 20-40 m/s, corresponding to Reynolds number of 3.1 × 10^5-6.2× 10^5. In control condition, the plasma actuator was installed symmetrically on the leading edge of the wing. Lift coefficient, drag coefficient, lift-to-drag ratio and pitching moment coefficient were tested with and without control for a range of angles of attack. The tested results indicate that an increase of 14.5% in maximum lift coefficient, a decrease of 34.2% in drag coefficient, an increase of 22.4% in maximum lift-to-drag ratio and an increase of 2° at stall angle of attack could be achieved compared with the baseline case. The effects of pulsed frequency, amplitude and chord Reynolds number were also investigated. And the results revealed that control efficiency demonstrated strong dependence on pulsed fre- quency. Moreover, the results of pitching moment coefficient indicated that the breakdown of lead- ing edge vortices could be delayed by plasma actuator at low pulsed frequencies.展开更多
基金supported by the National Natural Science Foundation of China – China (Nos. 51276197, 51207169 and 51336011)
文摘Experimental investigation of aerodynamic control on a 35° swept flying wing by means of nanosecond dielectric barrier discharge （NS-DBD） plasma was carried out at subsonic flow speed of 20-40 m/s, corresponding to Reynolds number of 3.1 × 10^5-6.2× 10^5. In control condition, the plasma actuator was installed symmetrically on the leading edge of the wing. Lift coefficient, drag coefficient, lift-to-drag ratio and pitching moment coefficient were tested with and without control for a range of angles of attack. The tested results indicate that an increase of 14.5% in maximum lift coefficient, a decrease of 34.2% in drag coefficient, an increase of 22.4% in maximum lift-to-drag ratio and an increase of 2° at stall angle of attack could be achieved compared with the baseline case. The effects of pulsed frequency, amplitude and chord Reynolds number were also investigated. And the results revealed that control efficiency demonstrated strong dependence on pulsed fre- quency. Moreover, the results of pitching moment coefficient indicated that the breakdown of lead- ing edge vortices could be delayed by plasma actuator at low pulsed frequencies.
