Experimental investigation of lift enhancement for flying wing aircraft using nanosecond DBD plasma actuators
he 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 obtain...
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| Published in | Plasma science & technology Vol. 19; no. 4; pp. 7 - 14 |
|---|---|
| Main Author | |
| Format | Journal Article |
| Language | English |
| Published |
IOP Publishing
01.04.2017
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| Subjects | |
| Online Access | Get full text |
| ISSN | 1009-0630 1009-0630 |
| DOI | 10.1088/2058-6272/aa57f1 |
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| Abstract | he 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 atf =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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| AbstractList | he 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 atf =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. 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. |
| Author | 姚军锴 周丹杰 何海波 何承军 史志伟 杜海 |
| AuthorAffiliation | Beijing Electro-mechanical Engineering Institute, Beijing 100074, People＇s Republic of China Nanjing University of Aeronautics and Astronautics, Nanjing 210016, People＇ s Republic of China |
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| Cites_doi | 10.2514/1.38232 10.2514/6.2016-1696 10.1088/1009-0630/17/6/11 10.2514/1.25368 10.1016/j.paerosci.2007.06.001 10.1146/annurev-fluid-121108-145550 10.2514/1.2929 10.1016/S0376-0421(00)00016-6 10.1016/j.cja.2015.02.006 10.2514/1.38113 10.1016/j.paerosci.2013.05.003 10.2514/1.33808 10.1016/S1369-8869(01)00005-2 |
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| Copyright | 2017 Hefei Institutes of Physical Science, Chinese Academy of Sciences and IOP Publishing |
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| DocumentTitleAlternate | Experimental investigation of lift enhancement for flying wing aircraft using nanosecond DBD plasma actuators |
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| Notes | Junkai YAO1, Danjie ZHOU1, Haibo HE1, Chengjun HE1, Zhiwei SHI2 and Hai DU2（1 Beijing Electro-mechanical Engineering Institute, Beijing 100074, People＇s Republic of China 2 Nanjing University of Aeronautics and Astronautics, Nanjing 210016, People＇ s Republic of China） dielectric barrier discharge, plasma, flying wing, flow control he 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 atf =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. 34-1187/TL Institute of Plasma Physics PST-2016-0111.R3 |
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| References | 13 15 Dmitriev V G (1) 2003 16 Lopera J (18) 2007 19 Patel M P (20) 2006 Esteban S (2) 2001 Roupassov D V (6) 2006 Wu Y (11) 2009 Duchmann A (22) 2010 3 4 Hu H Y (14) 2015 5 7 Takashima K (12) 2010 8 9 Han M H (17) 2015; 17 10 21 |
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| Snippet | he effects of the arrangement position and control parameters of nanosecond dielectric barrier discharge （NS-DBD） plasma actuators on lift enhancement for... The effects of the arrangement position and control parameters of nanosecond dielectric barrier discharge (NS-DBD) plasma actuators on lift enhancement for... |
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| SubjectTerms | DBD dielectric barrier discharge flow control flying wing plasma 实验 最大升力系数 激励器 等离子体控制 纳秒级 飞翼 飞行器 |
| Title | Experimental investigation of lift enhancement for flying wing aircraft using nanosecond DBD plasma actuators |
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