HyTRV标模下表面边界层稳定性特征

刘姝怡; 王傲; 段茂昌; 徐洋; 黄刚雷; 陈坚强

doi:10.11729/syltlx20240014

HyTRV标模下表面边界层稳定性特征

刘姝怡^{1, 2,},
王傲^{1, 2},
段茂昌^{1, 2},
徐洋³,
黄刚雷^{1, 2, ,},
陈坚强^{1, 2}

1.
空天飞行空气动力科学与技术全国重点实验室，绵阳　621000
2.
中国空气动力研究与发展中心计算空气动力研究所，绵阳　621000
3.
中国空气动力研究与发展中心超高速空气动力研究所，绵阳　621000

详细信息

作者简介:
刘姝怡: （1994—），女，云南宣威人，博士，助理研究员。研究方向：边界层转捩。E-mail：LSYNWPU@126.com

通讯作者:
黄刚雷: E-mail：huangganglei2021@163.com

中图分类号: V211.7
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出版历程
- 收稿日期: 2024-02-01
- 修回日期: 2024-02-20
- 录用日期: 2024-02-26
- 网络出版日期: 2024-05-06

Characteristics of boundary layer stability of HyTRV model bottom

LIU Shuyi^{1, 2,},
WANG Ao^{1, 2},
DUAN Maochang^{1, 2},
XU Yang³,
HUANG Ganglei^{1, 2, ,},
CHEN Jianqiang^{1, 2}

1.
State Key Laboratory of Aerodynamics, Mianyang　621000, China
2.
Computational Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang　621000, China
3.
Hypervelocity Aerodynamics Institute of China Aerodynamics Research and Development Center, Mianyang　621000, China

摘要

摘要: 高超声速转捩研究飞行器(Hypersonic Transition Research Vehicle, HyTRV)是为高超声速复杂三维边界层转捩研究设计的升力体标模，更接近真实飞行器外形。为深入认识HyTRV边界层稳定性特征及转捩机制，验证数值模拟和理论分析结果，本文在马赫6常规风洞中，采用红外热成像技术和高频压力传感器获得了0°和2°迎角时HyTRV标模下表面（迎风面）边界层转捩阵面及不稳定波演化特征，并与一维稳定性分析结果进行了对比。研究结果表明：迎角为2°时，标模下表面横流失稳区较0°迎角时缩小且后移，标模中心线处转捩先于两侧横流区。另外，横流区存在宽频的高频信号，信号幅值在转捩完成前达到饱和。该信号包含多频段扰动，多种扰动之间相互作用，使得频谱变宽，边界层最终转捩变为湍流。
- 升力体 /
- 横流失稳 /
- 高超声速风洞 /
- 边界层转捩 /
- e^N方法
Abstract: The HyTRV (Hypersonic Transition Research Vehicle) is designed for the study of hypersonic complex three-dimensional boundary layer transition, the shape of which is close to that of the real aircraft. The principal objective of this research is to gain deeper understanding of the stability characteristics and transition mechanism of the boundary layer over the HyTRV model and verify the results of numerical simulation and theoretical analysis. In the Mach 6 wind tunnel, the transition front and unstable wave evolution characteristics at the bottom of the HyTRV model, obtained by the infrared thermal imaging technology and high-frequency pressure sensors respectively, were compared with the results of one-dimensional stability analysis. At the angle of attack of 2 degrees, the instability crossflow region on the windward side, which is located after the front of transition at the centerline, shrinks and moves backwards compared to the results with zero angle of attack. Broadband high-frequency signals, containing multiple disturbances in different frequency bands, were found in the crossflow region. The interaction between various disturbances widens the frequency spectrum. Then the boundary layer appears to breakdown. The signal amplitude reaches saturation before the transition is complete.
- lifting body /
- crossflow instability /
- hypersonic wind tunnel /
- boundary layer transition /
- e^N method

HTML全文

图 3 Re_∞ = 2.0 × 10⁷ m⁻¹，基本流

Fig. 3 Re_∞ = 2.0 × 10⁷ m⁻¹，baseflow

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图 1 HyTRV标模

Fig. 1 HyTRV model

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图 2 传感器位置示意图

Fig. 2 The position of sensor

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图 4 不同Re_∞下的温升分布

Fig. 4 Temperature rise distribution under different Re_∞

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图 5 传感器安装位置温升曲线

Fig. 5 Temperature rise curve along the position of sensor

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图 6 Re_∞ = 1.5 × 10⁷ m⁻¹时，Kulite传感器测量信号功率谱密度分布

Fig. 6 Re_∞ = 1.5 × 10⁷ m⁻¹, PSD of Kulite

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图 7 Re_∞ = 1.5 × 10⁷ m⁻¹，PCB传感器测量信号功率谱密度分布

Fig. 7 Re_∞ = 1.5 × 10⁷ m⁻¹, PSD of PCB

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图 8 小波系数分布

Fig. 8 Wavelet coefficient

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图 9 双谱分析结果

Fig. 9 Bispectral analysis result

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图 10 不同Re_∞下的高频信号幅值演化曲线

Fig. 10 The amplitude evolution of high frequency signal at different Re_∞

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图 11 α = 2°，不同Re_∞下的标模表面温升分布

Fig. 11 α = 2°, Temperature rise distribution under different Re_∞

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图 12 α = 2°，Re_∞ = 2.0 × 10⁷ m⁻¹，基本流

Fig. 12 α = 2°, Re_∞ = 2.0 × 10⁷ m⁻¹, baseflow

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图 13 Re_∞ = 2.0 × 10⁷ m⁻¹时，Kulite功率谱密度分布

Fig. 13 Re_∞ = 2.0 × 10⁷ m⁻¹, PSD of Kulite

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图 14 Re_∞ = 2.0 × 10⁷ m⁻¹时，PCB传感器信号功率谱密度分布

Fig. 14 Re_∞ = 2.0 × 10⁷ m⁻¹, PSD of PCB

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图 15 小波系数分布

Fig. 15 Wavelet coefficient

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图 16 双谱分析结果（C4）

Fig. 16 Bispectral analysis result （C4）

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图 17 N值分布和最不稳定频率分布

Fig. 17 Distribution of N-factor and the most unstable frequency

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图 18 横流模态不稳定频域范围

Fig. 18 The frequency range of unstable crossflow mode

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图 19 第二模态不稳定频率范围

Fig. 19 The frequency range of unstable second mode

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表 1 实验工况

Table 1 Experimental conditions

马赫数Ma 迎角α/(°) Re_∞/(m⁻¹)

6 0 1.0 × 10⁷、1.5 × 10⁷、2.0 × 10⁷

6 2 1.5 × 10⁷、2.0 × 10⁷

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