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钝头旋成体背涡迎角效应的分区性态

齐中阳 王延奎 曹鹏

齐中阳, 王延奎, 曹鹏等 . 钝头旋成体背涡迎角效应的分区性态[J]. 北京航空航天大学学报, 2018, 44(10): 2134-2140. doi: 10.13700/j.bh.1001-5965.2018.0798
引用本文: 齐中阳, 王延奎, 曹鹏等 . 钝头旋成体背涡迎角效应的分区性态[J]. 北京航空航天大学学报, 2018, 44(10): 2134-2140. doi: 10.13700/j.bh.1001-5965.2018.0798
QI Zhongyang, WANG Yankui, CAO Penget al. Zonal behavior of angle of attack effects on vortices over blunt-slender body[J]. Journal of Beijing University of Aeronautics and Astronautics, 2018, 44(10): 2134-2140. doi: 10.13700/j.bh.1001-5965.2018.0798(in Chinese)
Citation: QI Zhongyang, WANG Yankui, CAO Penget al. Zonal behavior of angle of attack effects on vortices over blunt-slender body[J]. Journal of Beijing University of Aeronautics and Astronautics, 2018, 44(10): 2134-2140. doi: 10.13700/j.bh.1001-5965.2018.0798(in Chinese)

钝头旋成体背涡迎角效应的分区性态

doi: 10.13700/j.bh.1001-5965.2018.0798
基金项目: 

国家自然科学基金 11472028

国家自然科学基金 11721202

空气动力学国家重点实验室开放基金 SKLA20160101

航空科学基金 2016ZA51

详细信息
    作者简介:

    齐中阳  男, 博士研究生。主要研究方向:钝头旋成体大迎角的非对称流动

    王延奎  男, 博士, 教授, 博士生导师。主要研究方向:大迎角空气动力学

    通讯作者:

    王延奎, E-mail:wangyankui@buaa.edu.cn

  • 中图分类号: V221.3

Zonal behavior of angle of attack effects on vortices over blunt-slender body

Funds: 

National Natural Science Foundation of China 11472028

National Natural Science Foundation of China 11721202

the Open Fund from State Key Laboratory of Aerodynamics SKLA20160101

Aeronautical Science Foundation of China 2016ZA51

More Information
  • 摘要:

    为了实现空空导弹的高机动性,基于模型后体直径D以及试验风速的雷诺数ReD=1.54×105,通过风洞测力和测压试验对钝头旋成体背涡流动特性随迎角的演化形式进行了研究。根据对模型不同迎角下所受侧向力、截面压力分布以及截面侧向力系数随时间波动情况的分析,确定了不同迎角下的钝头旋成体背涡流动形式。以此划分了4个迎角分区:附着流动区(α≤10°)、对称涡流动区(10° < α≤20°)、定常非对称流动区(20° < α≤50°)和非定常非对称流动区(α>50°)。对各迎角分区的背涡流动特性进行了详细讨论。

     

  • 图 1  模型与人工扰动

    Figure 1.  Model and artificial perturbation

    图 2  模型在风洞中的安装

    Figure 2.  Model setup in wind tunnel

    图 3  侧向力系数随迎角的演化

    Figure 3.  Variation of side force coefficient with angle of attack

    图 4  不同迎角的截面侧向力系数随模型轴向x/D的演化

    Figure 4.  Variation of sectional side force coefficient with model axial x/D at different angles of attack

    图 5  α=5°时各截面压力分布曲线

    Figure 5.  Sectional pressure distribution curves at α=5°

    图 6  α=10°和α=20°时各截面压力分布曲线

    Figure 6.  Sectional pressure distribution curves at α=10° and α=20°

    图 7  α=40°和α=55°时各截面压力分布曲线

    Figure 7.  Sectional pressure distribution curves at α=40° and α=55°

    图 8  截面侧向力系数均方根值随迎角的演化

    Figure 8.  Variation of RMS of sectional side force with angle of attack

    图 9  不同迎角的瞬时截面侧向力系数随时间变化

    Figure 9.  Variation of transient sectional side force coefficient at different angles of attack with time

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出版历程
  • 收稿日期:  2017-12-25
  • 录用日期:  2018-03-23
  • 刊出日期:  2018-10-20

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