Infrared thermogram measurement experiment of hypersonic boundary-layer transition of a lifting body
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摘要: 在常规高超声速风洞中，开展了针对升力体模型的边界层转捩红外测量实验，研究了不同单位雷诺数和马赫数对升力体边界层转捩的影响规律，并与eN方法计算结果进行了对比。实验模型长度为800 mm，来流的单位雷诺数为0.46×107～3.94×107 m–1，马赫数为5～8，迎角为0°。通过大面积红外热图技术获得了模型表面温升分布，得到了边界层转捩阵面形状。实验结果表明：在升力体边界层中存在横流失稳和第二模态转捩；随着单位雷诺数增大，横流转捩效应增强，模型下表面和上表面温升增加，转捩阵面前移，转捩区域扩大；随着马赫数增大，横流转捩效应减弱，转捩位置后移，转捩区域显著减小；不同单位雷诺数和马赫数下的转捩N值比较接近，但上、下表面的转捩N值不同（下表面约为6，上表面约为2.5），侧缘在高单位雷诺数下会出现高频第二模态转捩。Abstract: For a lifting body model, the boundary layer transition infrared thermogram measurement experiment was carried out in the conventional hypersonic wind tunnel, and the influence of different unit Reynolds number and Mach number on the lifting body boundary layer transition was studied, which was compared with the calculation results of the eN method. The length of the experimental model is 800 mm, the unit Reynolds number is 0.46×107～3.94×107 m–1, the Mach number is 5～8, and the angle of attack is 0°. The transition position and transition front of the boundary layer on the surface of the model are obtained by the large-area infrared thermogram technology. The analysis of the experimental results shows that there are crossflow instability and the second mode transition in the boundary layer of the lifting body. As the unit Reynolds number increases, the crossflow transition effect increases, the temperature rise on the lower and upper surfaces of the model increases, the transition front moves forward, and the transition area expands; as the Mach number increases, the crossflow transition effect gradually weakens and the transition position moves downstream, and the transition area significantly shrinks back. Moreover, the transition N factor at different Mach numbers and unit Reynolds numbers are relatively close, but the N factors of the upper and lower surfaces are different. The lower surface is about 6, and the upper surface is about 2.5. The high-frequency second mode transition occurs in the side edge at high unit Reynolds numbers.
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Key words:
- lifting body /
- hypersonic wind tunnel /
- boundary layer transition /
- infrared thermogram
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图 10 不同雷诺数下表面的N等值线与风洞实验结果比较
Figure 10. N-factor distribution compared with wind tunnel test at different Reynolds numbers on the lower surface
图 11 不同雷诺数上表面的N等值线与风洞实验结果比较
Figure 11. N-factor distribution compared with wind tunnel test at different Reynolds numbers on the upper surface
图 12 不同马赫数下表面的N等值线与风洞实验结果比较
Figure 12. N-factor distribution compared with wind tunnel test at different Mach numbers on the lower surface
图 13 不同马赫数上表面的N等值线与风洞实验结果比较
Figure 13. N-factor distribution compared with wind tunnel test at different Mach numbers on the upper surface
图 15 侧缘第二模态N值分布（f=1150 kHz）
Figure 15. N-factor distribution of second mode at side leading-edge （f=1150 kHz）
表 1 实验状态
Table 1. Test conditions
编号 Ma∞ Re∞ /m–1 α /（°） 研究内容 1 6 0.46×107～3.94×107 0 雷诺数对下表面、
上表面转捩的影响2 5～8 1.00×107 0 马赫数对下表面、
上表面转捩的影响
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表 2 流场参数
Table 2. Parameters of flow field
Ma∞ p0/MPa T0/K p∞/Pa T∞/K Re∞/m–1 车次号 模型 5 0.50 381 988 64 0.99×107 190376 下表面 6 0.51 485 339 60 0.46×107 190362 下表面 6 1.11 487 726 60 0.98×107 190361 下表面 6 2.78 492 1740 60 2.38×107 190364 下表面 6 4.83 506 3030 61 3.94×107 190365 下表面 7 2.45 610 608 57 1.04×107 190350 下表面 8 4.4 724 436 52 0.99×107 190330 下表面 5 0.52 387 1020 65 1.00×107 190374 上表面 6 0.48 479 316 59 0.44×107 190355 上表面 6 1.10 489 715 60 0.96×107 190354 上表面 6 2.81 523 1780 64 2.18×107 190356 上表面 7 2.47 609 613 57 1.05×107 190353 上表面 8 4.37 733 433 53 0.97×107 190334 上表面
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