Abstract
In this study, a microsecond pulsed dielectric barrier discharge (μs-DBD) plasma actuator is utilized to improve the aerodynamic performance of a flying wing. The wind tunnel experiments were conducted by the μs-DBD plasma actuator at a high Reynolds number (Re = 2.61 × 106). The effects of discharge position and pulse frequency on the flow control performance were studied by force measurements. The particle image velocimetry test was used to reveal the influence of plasma actuation on the detailed velocity field at the suction side of the flying wing. Results show that plasma actuation can significantly improve the aerodynamic performance of the flying wing under high Reynolds number. The best flow control effect is obtained when the plasma actuator is mounted near stagnation point (0.1% C). There is an optimal excitation frequency (100 Hz) at Re = 2.61 × 106 (corresponding to the wind speed of 70 m/s), at which the flow instability can be effectively excited. In the optimal situation, the relative improvement of the maximum lift coefficient reaches 20.51% and the stall angle is delayed by 6°. The flow control performance is mainly achieved at the outer part of the wing because the flow separation develops gradually from the wing tip to the root. These experimental results contribute to the free flight test in the wind tunnel and the flight test in real air conditions.
Highlights
Compared with the conventional layout aircraft, the flying wing layout aircrafts have the outstanding advantages of high aerodynamic efficiency, light weight, large loading space, and good stealth performance and are favored by both military and civil applications all over the world.1,2 With the increasing use of the aviation field, the aircraft of flying wing layout seems to be the seed candidates for future development.3 Most of flying wing aircraft use tailless layout and swept wing with a blunt leading edge.4 This layout has good aerodynamic performance at high speed and small angle of attack (α)
The results of the flying wing with plasma actuation obtained in this paper provide an experimental basis for the free flight test in the wind tunnel and the flight test in real air conditions
The best flow control effects with the plasma actuation are within the position of c0 = ±0.5% with the maximum lift coefficient increased by 17% and the stall delayed by 5.2○
Summary
Compared with the conventional layout aircraft, the flying wing layout aircrafts have the outstanding advantages of high aerodynamic efficiency, light weight, large loading space, and good stealth performance and are favored by both military and civil applications all over the world. With the increasing use of the aviation field, the aircraft of flying wing layout seems to be the seed candidates for future development. Most of flying wing aircraft use tailless layout and swept wing with a blunt leading edge. This layout has good aerodynamic performance at high speed and small angle of attack (α). Compared with the conventional layout aircraft, the flying wing layout aircrafts have the outstanding advantages of high aerodynamic efficiency, light weight, large loading space, and good stealth performance and are favored by both military and civil applications all over the world.. With the increasing use of the aviation field, the aircraft of flying wing layout seems to be the seed candidates for future development.. Most of flying wing aircraft use tailless layout and swept wing with a blunt leading edge.. Most of flying wing aircraft use tailless layout and swept wing with a blunt leading edge.4 This layout has good aerodynamic performance at high speed and small angle of attack (α). At a large angle of attack, asymmetric boundary layer separation of the flying wing leads to great lift loss, drag enhancement, and deterioration of pitching characteristics.. At low speed and high angle of attack (such as taking off and landing), its aerodynamic performance is poor. At a large angle of attack, asymmetric boundary layer separation of the flying wing leads to great lift loss, drag enhancement, and deterioration of pitching characteristics. In addition, the flow separation causes the reduction of the control surface efficiency and maneuverability.
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