基于温敏漆的边界层转捩测量技术研究

黄辉; 熊健; 刘祥; 祝茂林; 李永红

doi:10.11729/syltlx20180144

基于温敏漆的边界层转捩测量技术研究

黄辉^1, ,,
熊健¹,
刘祥¹,
祝茂林²,
李永红¹

1.
中国空气动力研究与发展中心高速空气动力研究所, 四川绵阳 621000
2.
南京航空航天大学, 南京 210000

详细信息

作者简介:
黄辉(1985-), 男, 四川资阳人, 硕士, 工程师。研究方向:风洞测控技术。通信地址:四川省绵阳市二环路南段6号(621000).E-mail:285862216@qq.com

通讯作者:
黄辉, E-mail: 285862216@qq.com

中图分类号: V211.71
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- 文章访问数: 219
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出版历程
- 收稿日期: 2018-09-27
- 修回日期: 2018-12-11
- 刊出日期: 2019-04-24

Study of the boundary layer transition detection technique based on TSP

1.
High Speed Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang Sichuan 621000, China
2.
Nanjing University of Aeronautics and Astronautics, Nanjing 210000, China

摘要

摘要: 以自然层流翼型RAE5243模型为研究对象，在0.6m跨超声速风洞进行温敏漆（Temperature Sensitive Paint，TSP）转捩测量技术研究，在Ma0.73和Ma0.75条件下开展了模型基本外形和鼓包外形的转捩测量试验。针对缺乏定量分析手段的问题，提出基于温度梯度的转捩位置自动判定算法，包括图像预处理、转捩点定位与筛选和转捩位置计算3个步骤。模型温度分布及转捩测量结果表明：重复性试验结果偏差较小，验证了转捩测量结果的可靠性；相同马赫数条件下，鼓包外形转捩位置相对基本外形向后缘移动；相同外形条件下，Ma0.75的转捩位置相对Ma0.73向后缘移动。TSP试验结果与CFD计算结果吻合较好，变化趋势一致，检验了数值模拟方法的有效性。
- 温敏漆 /
- 边界层转捩测量 /
- 自然层流翼型 /
- 鼓包 /
- 温度分布
Abstract: By using the natural laminar airfoil RAE5243 as the research object, the TSP(Temperature Sensitive Paint) transition detection technique is studied in the 0.6m transonic and hypersonic wind tunnel in China Aerodynamics Research and Development Center. The transition detection tests of the model's baseline configuration with and without the shock control bump are conducted at Mach number 0.73 and 0.75, respectively. Focusing on the lack of quantitative analysis method, an automatic location algorithm based on the temperature gradient is proposed, which includes the image preprocessing, the transition point positioning and filtration, and the transition location's calculation. The model's temperature distribution and transition location under different test conditions are compared, and the deviations between repeatable transition detection tests' results are very small, which ensure the reliability of the technique. The transition location of the baseline configuration with the shock control bump is behind that of the baseline configuration at the same Mach number. The same model's transition location at Mach number 0.75 is behind that of 0.73. The TSP result and CFD result match well and the tendency is the same.
- TSP /
- boundary layer transition detection /
- natural laminar airfoil /
- shock control bump /
- temperature distribution

HTML全文

图 1 TSP校准曲线

Fig. 1 TSP calibration curves

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图 2 基于温度分布的转捩测量原理

Fig. 2 Principle of the transition detection based on temperature distribution

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图 3 基本外形与鼓包外形

Fig. 3 Baseline configuration and the configuration with shock control bump

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图 4 模型及测量设备

Fig. 4 Model and measuring equipment

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图 5 温度分布图像

Fig. 5 Temperature distribution images

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图 6 测压孔位置拟合曲线

Fig. 6 Pressure tap position fitting curve

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图 7 基本外形转捩位置(Ma=0.73, α=0°)

Fig. 7 Transition location of baseline configuration (Ma=0.73, α=0°)

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图 8 鼓包外形转捩位置(Ma=0.73, α=0°)

Fig. 8 Transition location of the configuration with shock control bump (Ma=0.73, α=0°)

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图 9 TSP与CFD转捩位置对比(Ma=0.73, α=0°)

Fig. 9 Transition locations comparison between TSP and CFD (Ma=0.73, α=0°)

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表 1 转捩位置判定结果

Table 1 Transition positioning result

模型	Ma	转捩位置 (全部)	转捩位置 (上半区域)	转捩位置 (下半区域)
基本外形	0.73 (TSP)	0.605c	0.605c	0.604c
	0.73 (TSP)	0.604c	0.604c	0.606c
	0.73 (CFD)	0.560c
	0.75 (TSP)	0.618c	0.615c	0.614c
	0.75 (CFD)	0.570c
鼓包外形	0.73 (TSP)	0.628c	0.628c	0.635c
	0.73 (TSP)	0.629c	0.628c	0.636c
	0.73 (CFD)	0.615c
	0.75 (TSP)	0.648c	0.642c	0.651c
	0.75 (CFD)	0.630c

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