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翼涡干扰前缘开孔被动控制数值研究

邹森 刘勇 王琦

邹森, 刘勇, 王琦. 翼涡干扰前缘开孔被动控制数值研究[J]. 应用数学和力学, 2019, 40(10): 1159-1168. doi: 10.21656/1000-0887.400028
引用本文: 邹森, 刘勇, 王琦. 翼涡干扰前缘开孔被动控制数值研究[J]. 应用数学和力学, 2019, 40(10): 1159-1168. doi: 10.21656/1000-0887.400028
ZOU Sen, LIU Yong, WANG Qi. Numerical Study on Passive Control of Airfoil-Vortex Interaction Based on Slotted Leading Edges[J]. Applied Mathematics and Mechanics, 2019, 40(10): 1159-1168. doi: 10.21656/1000-0887.400028
Citation: ZOU Sen, LIU Yong, WANG Qi. Numerical Study on Passive Control of Airfoil-Vortex Interaction Based on Slotted Leading Edges[J]. Applied Mathematics and Mechanics, 2019, 40(10): 1159-1168. doi: 10.21656/1000-0887.400028

翼涡干扰前缘开孔被动控制数值研究

doi: 10.21656/1000-0887.400028
基金项目: 国家自然科学基金(地区科学基金)(11962018); 航空科学基金项目(2018ZA56003);江西省教育厅科技项目(GJJ180511)
详细信息
    作者简介:

    邹森(1993—),男,硕士生(E-mail: 2019100412@mail.nwpu.edu.cn);刘勇(1979—)男,讲师,博士,硕士生导师(通讯作者. E-mail: liuyong@nchu.edu.cn).

  • 中图分类号: V211.3

Numerical Study on Passive Control of Airfoil-Vortex Interaction Based on Slotted Leading Edges

Funds: The National Natural Science Foundation of China(11962018)
  • 摘要: 开孔方法是一种简单的流动被动控制方法.为找到一种有效降低桨涡干扰效应的被动控制方法,以NACA 0012翼型作为研究对象,建立了4种前缘开孔的模型.在不同来流速度、涡的强度和干扰距离条件下,对4种前缘开孔模型和无孔的基准翼型进行了二维平行桨涡干扰(翼涡干扰)数值模拟,对比了升力系数的变化.结果表明:前缘开孔可以降低翼涡干扰效应,但对翼型升力系数有一定的影响;宽度为2.5%弦长的直孔能在翼型升力系数损失较小的情况下有效地降低翼涡干扰效应,且适用范围较广.
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出版历程
  • 收稿日期:  2019-01-10
  • 修回日期:  2019-01-24
  • 刊出日期:  2019-10-01

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