高超声速边界层感受性研究综述

江贤洋; 李存标

doi:10.11729/syltlx20160129

高超声速边界层感受性研究综述

doi: 10.11729/syltlx20160129

江贤洋^1,,
李存标^{1, 2, ,}

1.
北京大学工学院湍流与复杂系统国家重点实验室, 北京 100871
2.
先进航空发动机协同创新中心, 北京 100191

基金项目:

国家自然科学基金资助项目“高超声速边界层控制转捩研究” 11632002

“可压缩湍流的机理、模式及实验研究” 11521091

“壁面温度对高超声速边界层转捩影响的实验研究” 11602005

详细信息

作者简介:
江贤洋 (1989-), 男, 福建三明人, 博士研究生。研究方向:实验流体力学。通信地址:北京市海淀区北京大学工学院 (100871)。E-mail:xyjmh@pku.edu.cn

通讯作者:
李存标, E-mail: cblee@mech.pku.edu.cn

中图分类号: O354.4
计量
- 文章访问数: 501
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- 被引次数: 0
出版历程
- 收稿日期: 2016-09-02
- 修回日期: 2016-10-26
- 刊出日期: 2017-04-25

Review of research on the receptivity of hypersonic boundary layer

Jiang Xianyang^1
,,
Li Cunbiao^{1, 2
, ,}

1.
State Key Laboratory for Turbulence and Complex System, College of Engineering, Peking University, Beijing 100871, China
2.
Collaborative Innovation Center of Advanced Aero-Engines, Beijing 100191, China

摘要

摘要: 高超声速边界层感受性是边界层转捩预测与控制的关键环节，其对高超声速飞行器研究至关重要。目前关于高超声速边界层感受性的实验研究仍然十分匮乏，为了更好地理解高超声速边界层感受性过程并指导该领域的实验研究，文章梳理了近20年来国际上高超声速边界层感受性问题的研究内容，包括对自由流扰动和壁面扰动的感受性，并主要介绍了Fedorov的前缘感受性理论和模态转化机制。最后总结了自由流扰动中感受性的不同发展路径。
- 高超声速边界层 /
- 感受性 /
- 综述 /
- 理论研究 /
- 声波 /
- 粗糙元 /
- 壁面温度
Abstract: As a key aspect of transition prediction and control, receptivity process in hypersonic boundary layer is of great importance. However, it still has not been thoroughly understood, and is especially lacking in experimental verification. In this paper, two categories of disturbances are reviewed, namely, free-stream disturbance (acoustic, vertical, thermal perturbation, shock wave and particulates) and wall-induced disturbances (roughness, vibration, blowing and suction, surface heating and cooling). Mostly concerned are the theory of Fedorov about leading-edge receptivity and inter-modal exchange mechanism. In order to make the issue of receptivity more clearly understood, a compendious path diagram is sketched to describe paths to Mack modes.
- hypersonic boundary layer /
- receptivity /
- review /
- theory research /
- acoustic /
- roughness /
- wall temperature

HTML全文

图 1 高超声速边界层自由流扰动感受性动示意图^[22]

Figure 1. A schematic of the wave field in a hypersonic flow induced by free-stream disturbance^[22]

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图 2 边界层内不同模态波和RF的关系^[40]

Figure 2. The distribution of the phase velocities of boundary-layer wave modes as a function of RF obtained by the LST^[40]

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图 3 二维扰动的相速度和增长率随雷诺数变化

Figure 3. Phase speed of two-dimensional disturbances as a function of Reynolds number^[38]

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图 4 入射角与耦合系数关系^[38]

Figure 4. Coupling coefficient |C₀| vs. incident angle^[38]

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图 5 声波感受性示意图

Figure 5. Physical picture of receptivity to acoustic waves^[38]

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图 6 感受性系数的理论和实验对比^[38]

Figure 6. Receptivity coefficient comparison of theory and experiment^[38]

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图 7 不同迎角和频率对不同模态的感受性系数影响^[26]

Figure 7. Response coefficients for cases of different frequencies and different incident wave angles^[26]

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图 8 壁面冷却对转捩的影响^[49]

Figure 8. Experimental effect of wall cooling on transition^[49]

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图 9 不同壁面温度条件下压力脉动的对比^[26]

Figure 9. Pressure perturbation along the wall surface induced by free-stream fast acoustic waves of zero incident wave angle and different temperature boundary conditions (F=2.2×10^-4)^[26]

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图 10 温斑影响下的快模态流向速度沿y轴分布^[61]

Figure 10. A map of the streamwise velocity component of mode F generated by the α component of the temperature spot localized at a distance y₀ from the wall, M =5.6, R = 1219.5, stagnation temperature T₀= 470 K, T_w^*=T_ad^*^[61]

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图 11 高超声速边界层不稳定波激发的路径

Figure 11. Possible roadmap to unstable mode in hypersonic boundary layer (IR-ineraction)

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表 1 壁面温度对感受性及转捩的影响

Table 1. Effect of wall condition on transiton and receptiviy

研究者	模型	Ma	方法	壁面条件	结论
Fedrov et al.2003	平板	6	理论	绝热	感受性：慢声波/快声波≈50
Fedrov et al.2003	平板	6	理论	冷壁	快模态可能失稳
Ma & Zhong2001	平板	4.5	计算 DNS	绝热	等温比绝热对声波的感受性小
Ma & Zhong2001	平板	4.5	计算 DNS	等温	等温比绝热对声波的感受性小
Balakumar2015	楔形圆锥	6	计算	绝热	感受性：慢声波/快声波≈20
Balakumar2015	楔形圆锥	6	计算	冷却	冷却 (尖锥)：转捩提前
Kara et al.2007，2008	楔形直锥	6	计算	绝热	感受性：慢声波/快声波≈67
Kara et al.2007，2008	楔形直锥	6	计算	冷却	冷却时转捩提前
Blanchard 1995	裙锥	6	实验	绝热/冷却	冷却时转捩提前
Demetriades 1978	直锥	8	实验	T_w: 0.41~0.8	冷却时转捩提前
Lysenko & Maslov 1984	平板	2/4/6	实验	T_w: 0.3~1	冷却对声波没影响Mack第一模态稳定第二模态失稳
Stetson et al. 1989	直锥	8	实验	T_w=0.42	冷却时转捩提前Mack第二模态频率变高，增长率变大
Polivanov2011	平板	5.4	理论计算	冷却加热	冷却时转捩提前冷却位置影响转捩
Sidorenko et al. 2015	直锥	6	实验计算	局部冷却	抑制第二模态转捩延迟
Sidorenko et al. 2015	直锥	6	实验计算	局部加热	与局部冷却结果相反
Soudakov et al.2009	平板	6	计算DNS	温度跳跃	温度跳跃影响感受性
Sanator et al. 1965	尖锥	8.8	实验	T_w: 0.08~0.4	没有明显影响
注：T_w指壁面温度/绝热温度

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