基于TSP方法的自然层流机翼转捩位置测量

武宁; 唐鑫; 段卓毅; 张彦军

doi:10.11729/syltlx20190085

基于TSP方法的自然层流机翼转捩位置测量

doi: 10.11729/syltlx20190085

中国航空工业第一飞机设计研究院, 西安 710089

详细信息

作者简介:
武宁(1986-), 男, 宁夏吴忠人, 工程师。研究方向:飞机气动特性研究、CFD数值模拟、动力影响及减阻设计。通信地址:陕西省西安市阎良区人民东路1号(710089)。E-mail:wnxgdhk@163.com

通讯作者:
武宁 E-mail: wnxgdhk@163.com

中图分类号: V211.73
计量
- 文章访问数: 166
- HTML全文浏览量: 107
- PDF下载量: 11
- 被引次数: 0
出版历程
- 收稿日期: 2019-07-02
- 修回日期: 2019-11-11
- 刊出日期: 2020-12-25

Transition measurement for the nature-laminar wing based on TSP technique

The First Aircraft Institute of AVIC, Xi'an 710089, China

摘要

摘要: 为验证某层流机翼的设计，在荷兰DNW-HST风洞开展了高速风洞试验，采用TSP方法对机翼表面边界层转捩位置进行了测量。试验结果表明：TSP方法用于探测自然层流机翼表面转捩位置非常有效，显示结果中层流和湍流区域明显，转捩边界清晰易辨。同时发现，试验对机翼表面光洁度要求很高，试验结果对机翼表面污染非常敏感，高雷诺数下，受机翼前缘污染影响，试验效果不佳。
- 自然层流机翼 /
- 风洞试验 /
- TSP /
- 转捩
Abstract: In order to verify the design results of a laminar flow wing, a high-speed wind tunnel test was carried out in the DNW-HST wind tunnel in the Netherlands, and the transition position of the boundary layer on the wing surface was measured by the TSP method in the test. The experimental results show that the TSP method is very effective in detecting the transition position of the natural laminar airfoil surface. At the same time, it is found that the test has high requirements on the surface finish of the wing, and the test results are very sensitive to the surface pollution of the wing.
- nature-laminar wing /
- wing tunnel test /
- Temperature-Sensitive Paint(TSP) /
- transition

HTML全文

图 1 HST风洞中的翼身组合体模型

Figure 1. Wing-body model in HST wind tunnel

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图 2 风洞试验模型上的粗糙带和监测线

Figure 2. Strip and monitor line for wind tunnel model

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图 3 雷诺数为6.0×10⁶、不同马赫下机翼表面转捩图

Figure 3. Transition with different Mach numbers (Re=6.0×10⁶)

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图 4 马赫数为0.75、不同雷诺数下机翼表面转捩图

Figure 4. Transition with different Reynolds numbers (Ma=0.75)

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图 5 自由转捩与固定转捩对比

Figure 5. Comparison of free transition and forced transition

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图 6 风洞试验结果与CFD结果对比

Figure 6. Comparison of wind tunnel test results and CFD results

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图 7 被污染的机翼前缘

Figure 7. Contamination impact on the leading edge

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图 8 机翼表面测压孔附近喷涂效果

Figure 8. Irregularities around p-tap after screen layer application

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图 9 2种后处理方式结果对比

Figure 9. Comparison of two different postprocessing results

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