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

被引：0

作者：

Jiang Y. ^{[1
]}

Li J. ^{[1
]}

Yang Z. ^{[1
]}

机构：

[1] School of Aeronautics, Northwestern Polytechnical University, Xi'an

来源：

Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica | 2022年 / 43卷 / 11期

关键词：

data correction; high subsonic speed; numerical simulation; verification aircraft with laminar wing section; wind tunnel test;

D O I：

10.7527/S1000-6893.2021.26814

中图分类号：

学科分类号：

摘要：

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. © 2022 AAAS Press of Chinese Society of Aeronautics and Astronautics. All rights reserved.

引用

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