某层流机翼验证机风洞试验数据修正方法

doi:10.7527/S1000-6893.2021.26814

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某层流机翼验证机风洞试验数据修正方法

姜有旭, 李杰, 杨钊

西北工业大学航空学院, 西安 710072

收稿日期:2021-12-13 修回日期:2021-12-29 出版日期:2022-11-15 发布日期:2022-01-18
通讯作者: 李杰,E-mail:lijieruihao@nwpu.edu.cn E-mail:lijieruihao@nwpu.edu.cn
基金资助:
国家自然科学基金（11972304，12272312）；航空科学基金（2019ZA053005）

Data correction method of wind tunnel test for verification aircraft with laminar wing section

JIANG Youxu, LI Jie, YANG Zhao

School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China

Received:2021-12-13 Revised:2021-12-29 Online:2022-11-15 Published:2022-01-18
Supported by:
National Natural Science Foundation of China (11972304, 12272312); Aeronautical Science Foundation of China (2019ZA053005)

摘要/Abstract

摘要： 高亚声速条件下机翼层流特性对雷诺数非常敏感，风洞试验雷诺数与飞行雷诺数有较大差异，需要对验证机风洞试验数据进行合理修正。针对验证机对雷诺数效应敏感的特点，首先总结并对比了基于经验公式和基于数值模拟的风洞试验气动力系数雷诺数效应修正方法的优缺点和适用性，并给出了风洞试验中伪雷诺数效应和模型差异等的影响，为验证机试验数据修正提供了思路。然后结合变雷诺数数值模拟对验证机气动特性进行雷诺数效应影响规律研究。最后使用基于变雷诺数数值模拟的试验数据修正方法将验证机高低速风洞试验结果由低雷诺数向高雷诺数修正。结果表明：变雷诺数数值模拟风洞试验数据修正方法对层流机翼验证机高低速风洞试验数据修正效果良好，为验证机精细设计提供数据支撑。

关键词: 层流机翼验证机, 数据修正, 高亚声速, 数值模拟, 风洞试验

Abstract: The laminar flow characteristics of wings at a high subsonic speed are sensitive to Reynolds number, while the Reynolds number of the wind tunnel test is considerably different from that of flight, necessitating reasonable correction of the wind tunnel test data of the verification aircraft. This paper first summarizes and compares the advantages, disadvantages and applicability of Reynolds number effect correction methods based on the empirical formula and numerical simulation in the aerodynamic coefficients correction of wind tunnel test data. The influence of pseudo Reynolds number effect and model difference in wind tunnel tests providing ideas for the verification aircraft test data correction is then discussed. Combined with the numerical simulation of the variable Reynolds number, the influence law of Reynolds number on the aerodynamic characteristics of the verification aircraft is studied. Finally, the test data correction method based on the variable Reynolds number numerical simulation is used to correct the high and low speed wind tunnel test results from low Reynolds numbers to high Reynolds numbers. The results show that the variable Reynolds number numerical simulation wind tunnel test data correction method has a good effect on high and low speed wind tunnel test data of the verification aircraft with the laminar wing section, therefore providing data support for detailed design of the verification aircraft.

Key words: verification aircraft with laminar wing section, data correction, high subsonic speed, numerical simulation, wind tunnel test

中图分类号:

V211

姜有旭, 李杰, 杨钊. 某层流机翼验证机风洞试验数据修正方法[J]. 航空学报, 2022, 43(11): 526814-526814.

JIANG Youxu, LI Jie, YANG Zhao. Data correction method of wind tunnel test for verification aircraft with laminar wing section[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(11): 526814-526814.

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某层流机翼验证机风洞试验数据修正方法

Data correction method of wind tunnel test for verification aircraft with laminar wing section

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