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飞行器尾涡对的不稳定性建模

陈俪芳 王志博 孙刚

陈俪芳, 王志博, 孙刚. 飞行器尾涡对的不稳定性建模[J]. 应用数学和力学, 2016, 37(8): 863-872. doi: 10.21656/1000-0887.370059
引用本文: 陈俪芳, 王志博, 孙刚. 飞行器尾涡对的不稳定性建模[J]. 应用数学和力学, 2016, 37(8): 863-872. doi: 10.21656/1000-0887.370059
CHEN Li-fang, WANG Zhi-bo, SUN Gang. Instability of Aircraft Multiple Trailing Vortex Pairs[J]. Applied Mathematics and Mechanics, 2016, 37(8): 863-872. doi: 10.21656/1000-0887.370059
Citation: CHEN Li-fang, WANG Zhi-bo, SUN Gang. Instability of Aircraft Multiple Trailing Vortex Pairs[J]. Applied Mathematics and Mechanics, 2016, 37(8): 863-872. doi: 10.21656/1000-0887.370059

飞行器尾涡对的不稳定性建模

doi: 10.21656/1000-0887.370059
基金项目: 国家重点基础研究发展计划(973计划)(2014CB744802)
详细信息
    作者简介:

    陈俪芳(1990—),女,硕士生(E-mail: chenlf14@fudan.edu.cn);王志博(1983—),男,工程师,博士(E-mail: wwzb3@163.com);孙刚(1966—),男,教授,博士,博士生导师(通讯作者. E-mail: Gang_sun@fudan.edu.cn).

  • 中图分类号: O355

Instability of Aircraft Multiple Trailing Vortex Pairs

Funds: The National Basic Research Program of China (973 Program)(2014CB744802)
  • 摘要: 为了确定飞行器尾流的保持距离和诱导失稳运动性质,首先在一阶近似BiotSavart定律的基础上,推导了任意多个涡对的诱导运动模型,进而利用线性组合方法得到涡系诱导运动的对称以及反对称模态,并结合模态矩阵特征值的性质描述对称分布涡系的稳定性.因为尾涡结构的不稳定性依赖于相应的模态矩阵特征值的取值, 所以在利用对称分布的二涡对的模态验证所推导的模态矩阵理论的正确性的基础上, 进一步给出了三涡对的模态矩阵对应的失稳模态. 理论推导和特征值的计算显示随着涡丝数量的不断增加, 三涡系的不稳定性增强, 并且涡系对扰动的放大作用增强.
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  • 被引次数: 0
出版历程
  • 收稿日期:  2016-03-02
  • 修回日期:  2016-03-13
  • 刊出日期:  2016-08-15

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