Plasma Aerodynamic Actuation Based Corner Separation Control in a Compressor Cascade

Wu, Yun; Li, Yinghong; Zhou, Min; Changbing, Su; Song, Huimin; Zhu, Jin

doi:10.2514/6.2009-4070

Cited by 3 publications

(2 citation statements)

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“…The NS-DBD plasma actuator acts in a different way than the AC-DBD. While discharge occurs, instead of accelerating the air though electric field, the NS-DBD plasma actuator heats the air around two electrodes, causing a pressure jump and creating a shock wave, thus pushing the surrounding air to accelerate and induce the momentum exchange [11][12][13][14][15].…”

Section: Introductionmentioning

confidence: 99%

Experimental investigation of lift enhancement for flying wing aircraft using nanosecond DBD plasma actuators

Yao¹,

Zhou²,

He³

et al. 2017

Plasma Sci. Technol.

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The effects of the arrangement position and control parameters of nanosecond dielectric barrier discharge (NS-DBD) plasma actuators on lift enhancement for flying wing aircraft were investigated through wind tunnel experiments at a flow speed of 25 m s −1 . The aerodynamic forces and moments were obtained by a six-component balance at angles of attack ranging from −4°to 28°. The lift, drag and pitching moment coefficients were compared for the cases with and without plasma control. The results revealed that the maximum control effect was achieved by placing the actuator at the leading edge of the inner and middle wing, for which the maximum lift coefficient increased by 37.8% and the stall angle of attack was postponed by 8°compared with the plasma-off case. The effects of modulation frequency and discharge voltage were also investigated. The results revealed that the lift enhancement effect of the NS-DBD plasma actuators was strongly influenced by the modulation frequency. Significant control effects were obtained at f=70 Hz, corresponding to F + ≈1. The result for the pitching moment coefficient demonstrated that the plasma actuator can induce the reattachment of the separation flows when it is actuated. However, the results indicated that the discharge voltage had a negligible influence on the lift enhancement effect.

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Section: Introductionmentioning

confidence: 99%

Experimental investigation of lift enhancement for flying wing aircraft using nanosecond DBD plasma actuators

Yao¹,

Zhou²,

He³

et al. 2017

Plasma Sci. Technol.

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“…This new three-electrode geometry actuator may intensify the flow control ability obviously. It has been demon-strated that the nanosecond discharge could be used in some areas, such as the corner separation control of compressor cascade, [24] stall margin extension in an axial compressor, [25] oblique shock wave control, [26][27][28] and flow separation control for two-dimensional airfoil. [29,30] Great progress has been made in nanosecond discharge plasma flow control.…”

Section: Introductionmentioning

confidence: 99%

Wind tunnel experiments on flow separation control of an Unmanned Air Vehicle by nanosecond discharge plasma aerodynamic actuation

Chen

Liang

2016

Chinese Phys. B

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Plasma flow control (PFC) is a new kind of active flow control technology, which can improve the aerodynamic performances of aircrafts remarkably. The flow separation control of an unmanned air vehicle (UAV) by nanosecond discharge plasma aerodynamic actuation (NDPAA) is investigated experimentally in this paper. Experimental results show that the applied voltages for both the nanosecond discharge and the millisecond discharge are nearly the same, but the current for nanosecond discharge (30 A) is much bigger than that for millisecond discharge (0.1 A). The flow field induced by the NDPAA is similar to a shock wave upward, and has a maximal velocity of less than 0.5 m/s. Fast heating effect for nanosecond discharge induces shock waves in the quiescent air. The lasting time of the shock waves is about 80 μs and its spread velocity is nearly 380 m/s. By using the NDPAA, the flow separation on the suction side of the UAV can be totally suppressed and the critical stall angle of attack increases from 20° to 27° with a maximal lift coefficient increment of 11.24%. The flow separation can be suppressed when the discharge voltage is larger than the threshold value, and the optimum operation frequency for the NDPAA is the one which makes the Strouhal number equal one. The NDPAA is more effective than the millisecond discharge plasma aerodynamic actuation (MDPAA) in boundary layer flow control. The main mechanism for nanosecond discharge is shock effect. Shock effect is more effective in flow control than momentum effect in high speed flow control.

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Aerodynamic performance enhancement of a flying wing using nanosecond pulsed DBD plasma actuator

Han

Niu

et al. 2015

Chinese Journal of Aeronautics

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Plasma Aerodynamic Actuation Based Corner Separation Control in a Compressor Cascade

Cited by 3 publications

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Experimental investigation of lift enhancement for flying wing aircraft using nanosecond DBD plasma actuators

Experimental investigation of lift enhancement for flying wing aircraft using nanosecond DBD plasma actuators

Wind tunnel experiments on flow separation control of an Unmanned Air Vehicle by nanosecond discharge plasma aerodynamic actuation

Aerodynamic performance enhancement of a flying wing using nanosecond pulsed DBD plasma actuator

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