| 多相等离子体气动激励抑制翼型失速分离的实验 |
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| 引用本文： | 梁华,李应红,宋慧敏,吴云,贾敏,马清源.多相等离子体气动激励抑制翼型失速分离的实验[J].航空动力学报,2011,26(4):867-873. |
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| 作者姓名： | 梁华 李应红 宋慧敏 吴云 贾敏 马清源 |
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| 作者单位： | 1. 中国人民解放军空军第五飞行学院,甘肃,武威,733003
2. 空军工程大学工程学院航空等离子体动力学实验室,西安,710038 |
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| 摘 要： | 开展了多相等离子体气动激励抑制NACA0015翼型失速分离的实验,详细研究了翼型升阻特性随激励电压、激励相角、输入电压波形和占空比等激励参数的影响.研究表明:雷诺数Re=4.9×105(来流速度60m/s)时,多相等离子体气动激励可有效抑制NACA0015翼型吸力面的流动分离,将翼型临界失速攻角提高2°;相位对流动控制...
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| 关 键 词： | 等离子体流动控制 多相等离子体气动激励 翼型 失速分离 升阻特性 |
| 收稿时间： | 2010/3/25 0:00:00 |
| 修稿时间： | 2010/12/8 0:00:00 |
Experimental investigation on airfoil stall separation suppression by multiphase plasma aerodynamic actuation |
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| LIANG Hu,LI Ying-hong,SONG Hui-min,WU Yun,JIA Min and MA Qing-yuan.Experimental investigation on airfoil stall separation suppression by multiphase plasma aerodynamic actuation[J].Journal of Aerospace Power,2011,26(4):867-873. |
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| Authors: | LIANG Hu LI Ying-hong SONG Hui-min WU Yun JIA Min and MA Qing-yuan |
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| Institution: | The Fifth Flight College of the Air Force, The Chinese People's Liberation Army,Wuwei Gansu 733003,China;Laboratory of Aero Plasma Dynamics,The Engineering Institute, Air Force Engineering University,Xi'an 710038,China;Laboratory of Aero Plasma Dynamics,The Engineering Institute, Air Force Engineering University,Xi'an 710038,China;Laboratory of Aero Plasma Dynamics,The Engineering Institute, Air Force Engineering University,Xi'an 710038,China;Laboratory of Aero Plasma Dynamics,The Engineering Institute, Air Force Engineering University,Xi'an 710038,China;Laboratory of Aero Plasma Dynamics,The Engineering Institute, Air Force Engineering University,Xi'an 710038,China |
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| Abstract: | Experiments on NACA0015 airfoil stalling separation control based on multiphase plasma aerodynamic actuation were performed in the paper.The effects of the plasma actuation voltage amplitude,phase,input waveform and duty cycle on the lift and drag of the airfoil were examined specifically.The results show that,when the Reynolds number is 4.9 ×105,multiphase plasma aerodynamic actuation can suppress flow separation very well.The critical stalling attack angle of NACA0015 airfoil can increase by 2°.The flow suppression effect is not sensitive to phase difference.The separated flow can be suppressed when the voltage amplitude and duty cycle reach their threshold values.Once the separated flow is suppressed,the actuation voltage magnitude maintaining flow attachment could be reduced significantly.The research can lay a foundation for the mechanism of multiphase plasma flow control. |
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| Keywords: | plasma flow control multiphase plasma aerodynamic actuation airfoil stall separation lift and drag property |
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