带扰动块的细长旋成体背部绕流数值模拟

刘克奇; 李国辉; 张浩南; 张宴嘉

doi:10.13700/j.bh.1001-5965.2020.0676

带扰动块的细长旋成体背部绕流数值模拟

doi: 10.13700/j.bh.1001-5965.2020.0676

空军航空大学航空作战勤务学院, 长春 130000

详细信息

通讯作者:
李国辉, E-mail: ghleeauaf@sina.com

中图分类号: V221;TJ760
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- 文章访问数: 311
- HTML全文浏览量: 46
- PDF下载量: 78
- 被引次数: 0
出版历程
- 收稿日期: 2020-12-02
- 录用日期: 2021-01-30
- 网络出版日期: 2021-07-20

Numerical simulation of flow around slender body with disturbing block

Aviation Operations Service Academy, Aviation University Air Force, Changchun 130000, China

More Information

Corresponding author: LI Guohui, E-mail: ghleeauaf@sina.com

摘要

摘要:
为了更好地了解细长旋成体背部绕流非对称涡的形成机理，研究了头部带扰动块对细长旋成体背部绕流结构的影响，通过雷诺平均Navier-Stokes（RANS）法对细长旋成体模型在攻角5°~60°范围内进行仿真。在攻角分别为20°和30°时对是否添加扰动块模型进行对比，分析了不同截面绕流沿轴向位置的发展，提出了验证拓扑结构的一种方法，找到了各流态下奇点的位置，通过涡核位置对模型背部绕流的发展进行了分析。研究表明：添加已知规则扰动块可以加快各绕流结构间的转换速度，使非对称涡产生的攻角减小。
- 绕流结构 /
- 细长旋成体 /
- 非对称流动 /
- 鞍点 /
- 拓扑结构
Abstract:
In this paper, the influence of the head disturbance block on the structure of the flow around the back of the slender body is studied. The slender body model is simulated at the angle of attack of 5°-60° through numerical simulation. The numerical calculation method selected is the Reynolds Average Navier-Stokes (RANS) method. This paper mainly compares whether to add a disturbance block model at an angle of attack of α=20°, 30°, analyzes the development of the flow around different sections along with the axial position, proposes a method to verify the topological structure, and finds the position of the singularity in each flow state. The position of the vortex core is used to analyze the development of the flow around the back of the model. It is found that the premise of adding a known regular disturbance block can speed up the conversion speed between the surrounding flow structures, and will reduce the angle of attack generated by the asymmetric vortex.
- surrounding flow structure /
- slender body /
- asymmetric flow /
- saddle point /
- topological structure

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图 1 尖拱-圆柱形细长旋成体模型

Figure 1. Pointed arch-cylindrical elongated slender body model

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图 2 计算域及网格划分

Figure 2. Computational domain and mesh division

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图 3 截面侧向力系数对比

Figure 3. Comparison of lateral force coefficients

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图 4 平均x涡量等值线

Figure 4. Mean x vorticity contour

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图 5 截面侧向力系数曲线

Figure 5. Cross-section lateral force coefficient curves

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图 6 物面压力轴向分布曲线

Figure 6. Axial distribution curves of surface pressure

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图 7 速度矢量分布

Figure 7. Velocity vector distribution

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图 8 细长旋成体绕流拓扑结构

Figure 8. Topological structure of flow around slender body

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图 9 壁面切向速度曲线

Figure 9. Tangential speed curves

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图 10 空间鞍点的纵向与横向位置

Figure 10. Vertical and horizontal positions of saddle point in space

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图 11 涡核位置

Figure 11. Vortex core position

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