纳秒脉冲等离子体分离流控制频率优化及涡运动过程分析
发布时间：2018-11-28 15:54
【摘要】：将纳秒脉冲驱动的介质阻挡放电等离子体激励器应用到NASA SC(2)-0712翼型上,在迎角分别为15°和20°时,开展了在不同雷诺数下的分离流动控制研究。通过模型表面静压测量,得到了不同激励频率下的分离流动控制效果。对翼型表面压力进行分布积分,得到了在不同雷诺数和激励频率下的升力系数,表明分离流的控制效果有一个较宽的激励频率范围,只要激励频率落在相应的频带范围内,均能实现有效的分离抑制。流动显示结果表明,分离流的控制在瞬时表现为放电后可形成大尺度旋涡拟序结构。旋涡的周期性产生、运动和演化造成了分离剪切流动的动态变化过程,从而促进了高/低速气流的动态掺混。
[Abstract]:The dielectric barrier discharge plasma exciter driven by nanosecond pulse is applied to the NASA SC (_ 2)-0712 airfoil. The separation flow control under different Reynolds numbers is studied at 15 掳and 20 掳of attack respectively. By measuring the static pressure on the surface of the model, the control effect of separated flow at different excitation frequencies is obtained. By integrating the surface pressure of the airfoil, the lift coefficients at different Reynolds numbers and excitation frequencies are obtained. The results show that the control effect of the separation flow has a wide excitation frequency range, as long as the excitation frequency falls within the corresponding frequency band, Can achieve effective separation inhibition. The flow display results show that the control of the separation flow can form a large scale vortex sequence structure after transient discharge. The periodic generation, movement and evolution of the vortex lead to the dynamic variation process of the separated shear flow, thus promoting the dynamic mixing of the high / low velocity flow.
【作者单位】： 南京航空航天大学航空宇航学院;
【基金】：国家自然科学基金(11532007) 中央高校基本科研业务费专项资金(NP2014605) 江苏省研究生培养创新工程(KYLX_0216) 南京航空航天大学基本科研业务费资助项目(NS2013013);南京航空航天大学研究生创新基地(实验室)开放基金(kfjj201401)~~
【分类号】：V211
[Abstract]:The dielectric barrier discharge plasma exciter driven by nanosecond pulse is applied to the NASA SC (_ 2)-0712 airfoil. The separation flow control under different Reynolds numbers is studied at 15 掳and 20 掳of attack respectively. By measuring the static pressure on the surface of the model, the control effect of separated flow at different excitation frequencies is obtained. By integrating the surface pressure of the airfoil, the lift coefficients at different Reynolds numbers and excitation frequencies are obtained. The results show that the control effect of the separation flow has a wide excitation frequency range, as long as the excitation frequency falls within the corresponding frequency band, Can achieve effective separation inhibition. The flow display results show that the control of the separation flow can form a large scale vortex sequence structure after transient discharge. The periodic generation, movement and evolution of the vortex lead to the dynamic variation process of the separated shear flow, thus promoting the dynamic mixing of the high / low velocity flow.
【作者单位】： 南京航空航天大学航空宇航学院;
【基金】：国家自然科学基金(11532007) 中央高校基本科研业务费专项资金(NP2014605) 江苏省研究生培养创新工程(KYLX_0216) 南京航空航天大学基本科研业务费资助项目(NS2013013);南京航空航天大学研究生创新基地(实验室)开放基金(kfjj201401)~~
【分类号】：V211
【参考文献】
相关期刊论文 前8条
1 Zhao Guangyin;Li Yinghong;Liang Hua;Han Menghu;Wu Yun;;Flow separation control on swept wing with nanosecond pulse driven DBD plasma actuators[J];Chinese Journal of Aeronautics;2015年02期
2 吴云;李应红;;等离子体流动控制研究进展与展望[J];航空学报;2015年02期
3 赵光银;李应红;梁华;化为卓;韩孟虎;;纳秒脉冲表面介质阻挡等离子体激励唯象学仿真[J];物理学报;2015年01期
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