钝头旋成体背涡迎角效应的分区性态

齐中阳; 王延奎; 曹鹏

doi:10.13700/j.bh.1001-5965.2018.0798

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

齐中阳^{1, 2},
王延奎^{1, 2, ,},
曹鹏³

1.
空气动力学国家重点实验室, 绵阳 621000
2.
北京航空航天大学航空科学与工程学院, 北京 100083
3.
上海航天控制技术研究所, 上海 200233

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
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- 被引次数: 0
出版历程
- 收稿日期: 2017-12-25
- 录用日期: 2018-03-23
- 网络出版日期: 2018-10-20

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

QI Zhongyang^{1, 2},
WANG Yankui^{1, 2
, ,},
CAO Peng³

1.
State Key Laboratory of Aerodynamics, Mianyang 621000, China
2.
School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100083
3.
Shanghai Institute of Spaceflight Control Technology, Shanghai 200233, China

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

Corresponding author: WANG Yankui, E-mail:wangyankui@buaa.edu.cn

摘要

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Re_D=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。
- 钝头旋成体 /
- 背涡结构 /
- 迎角效应 /
- 非对称流动 /
- 大迎角空气动力学
Abstract:
In order to achieve the high maneuverability of the air-to-air missile, the flow characteristics of vortices over the blunt-slender body at different angles of attack were studied by wind tunnel forces and pressure test in this paper. The Reynolds number is set as Re_D=1.54×10⁵, based on oncoming free-stream velocity and the diameter of the blunt-slender body (D). The flow structures over the blunt-slender body were determined at different angles of attack according to the analysis of side forces, sectional pressure distribution and the variation histories of the sectional side force with time. Four regions about the angles of attack are divided, i.e., attached-flow region (α ≤ 10°), symmetric-flow region (10° < α ≤ 20°), steady asymmetric-flow region (20° < α ≤ 50°) and unsteady asymmetric-flow region (α>50°). The flow characteristics of vortices over the blunt-slender body at different angles of attack were discussed in detail.
- blunt-slender body /
- vortex structure /
- angle of attack effects /
- asymmetric flow /
- high angle of attack aerodynamics

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图 1 模型与人工扰动

Figure 1. Model and artificial perturbation

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图 2 模型在风洞中的安装

Figure 2. Model setup in wind tunnel

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图 3 侧向力系数随迎角的演化

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

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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

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图 5 α=5°时各截面压力分布曲线

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

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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°

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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°

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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

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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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