高速升力体腹部流向涡的全局稳定性特征

张彬; 李晓虎; 涂国华; 黄文锋; 陈坚强

doi:10.13224/j.cnki.jasp.20240402

高速升力体腹部流向涡的全局稳定性特征

doi: 10.13224/j.cnki.jasp.20240402

空天飞行空气动力科学与技术全国重点实验室，四川绵阳 621000

基金项目: 国家自然科学基金（92052301）

详细信息

作者简介:
张彬（1996-），男，博士生，研究方向为边界层转捩。E-mail：fullwings@163.com

通讯作者:
陈坚强（1966-），研究员，博士，研究方向为复杂流动数值模拟及流动机理。E-mail：chenjq@cardc.cn

中图分类号: V211.3；O355
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出版历程
- 收稿日期: 2024-06-20
- 网络出版日期: 2025-11-29

Global stability of streamwise vortices over a lifting body

State Key Laboratory of Aerodynamics，Mianyang Sichuan 621000，China

摘要

摘要:
对高速升力体飞行器流向涡的基本流特征及稳定性特征进行了研究。层流基本流由直接求解Navier-Stokes（N-S）方程计算得到，稳定性特征采用二维全局稳定性分析方法（BiGlobal）获取。来流马赫数为6，单位雷诺数为1.0×10⁷/m，静温为79 K，攻角为0°。计算结果表明：升力体表面存在多个复杂流动区域，表面流线在相对高压区分散，在相对低压区汇聚，形成附着线与流向涡交替分布的结构，其中位于腹部的流向涡结构形成最早，尺度最大。稳定性分析结果表明：升力体腹部流向涡区域由于剪切的复杂性，存在多支不稳定模态，根据相速度的大小可以分为内模态与外模态，其中外模态更不稳定，根据形函数的对称性可以分为对称模态与反对称模态，两者的增长率及相速度接近。不稳定模态的失稳频率范围在0～100 kHz，相比于已知的有攻角锥及椭圆锥的流向涡的失稳频率更低。采用基于全局稳定性的e^N方法对流向涡区域不稳定模态增长率进行积分，结果表明不稳定模态的主导频率随着下游逐渐增大，最不稳定的模态为形函数峰值位于流向涡肩部的外模态。
- 升力体 /
- 流向涡 /
- 全局稳定性 /
- 边界层转捩 /
- N值
Abstract:
The global stability characteristics of the streamwise vortices over a lifting body were studied. Laminar flow was calculated by direct numerical simulation of Navier-Stokes (N-S) equation, and the stability characteristics were obtained by two-dimensional global stability analysis method (BiGlobal). The Mach number of incoming flow was 6, the unit Reynolds number was 1.0×10⁷/m, the static temperature was 79 K, and the angle of attack was 0°. The results showed that there were multiple complex flow regions on the lifting body surface, and the streamlines near wall dispersed in the relatively high pressure region and converged in the relatively low pressure region, forming an alternating distribution of attachment line and streamwise vortex. The streamwise vortex located in the lower surface emerged first and had the largest scale. The stability analysis results showed that, there were many unstable modes in the vortex region due to the complex shear layer. According to the magnitude of phase velocity, these can be divided into inner modes and outer modes, and the outer modes were more unstable. According to the symmetry of eigenfunction, they can be divided into symmetric modes and anti-symmetric modes, and their growth rates and phase velocities were close. The instability frequency of the unstable modes ranged from 0 kHz to 100 kHz, lower than that of the vortex on inclined cones and elliptical cones. The e^N method based on global stability was used to integrate the N value of unstable modes in the vortex region. The results showed that the dominant frequency increased gradually with the downstream. The most unstable mode was the outer mode whose eigenfunction peaked at the vortex shoulder.
- lifting body /
- streamwise vortices /
- global stability /
- boundary-layer transition /
- N factor

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图 1 HyTRV模型形状及尺寸

Figure 1. Shape and dimension of HyTRV

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图 2 间隔10点显示的计算网格

Figure 2. Computational mesh with grid points displayed at intervals of 10

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图 3 网格收敛性

Figure 3. Grid convergence

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图 4 稳定性分析的网格无关性

Figure 4. Grid independence of stability analysis

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图 5 升力体表面的流向速度云图（X^*=300, 500, 700, 900, 1100, 1300, 1500 mm）及壁面极限流线

Figure 5. Streamwise velocity contours of lifting body （X^*=300, 500, 700, 900, 1100, 1300, 1500 mm） and wall extremity streamline

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图 6 速度剪切云图

Figure 6. Contour of velocity shear

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图 7 速度剪切随流向变化

Figure 7. Velocity shear varing along the streamwise direction

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图 8 流向涡区域不同站位处的速度剪切峰值

Figure 8. Peak velocity shear at different stations in the streamwise vortex region

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图 9 X^*=800 mm处的重要不稳定模态

Figure 9. Important unstable modes at X^* = 800 mm

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图 10 无量纲温度扰动形函数

Figure 10. Normalized temperature disturbance shape functions

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图 11 不同站位处的不稳定模态特征

Figure 11. Characteristics of unstable modes at different stations

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图 12 O2及O3模态的演化

Figure 12. Evolution of O2 and O3 modes

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图 13 不稳定模态N值曲线

Figure 13. N value curves of unstable mode

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表 1 已知典型流向涡的稳定性特征

Table 1. Stability characteristics of known typical streamwise vortices

作者	年份	模型	来流条件	模态失稳频率范围/Hz	主导模态及频率
Zhang等^[29]	2022	5°攻角钝锥	飞行工况	0～500	对称Mack模态（200 kHz ）
Chen等^[2]	2022	HyTRV腰部流向涡	风洞工况	0～170	外模态（70 kHz）
Li等^{[10, 27]}和陈曦等^[9]	2020—2021	6°攻角圆锥	风洞工况	0～500	反对称模态（85 kHz）
Choudhari等^[7]	2020	HIFiRE-5椭圆锥	飞行工况	0～400	反对称模态（150～200 kHz）
Paredes等^[21]	2016	HIFiRE-5椭圆锥	飞行工况（飞行高度为21.8 km）	0～550	对称模态
Paredes等^[22]	2014	HIFiRE-5椭圆锥	飞行工况（飞行高度为33 km）	0～300	对称模态

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