Method of test data correction for wide-body aircraft in high speed wind tunnel

被引：0
作者：
Liu D. [1 ]
Xiong G. [1 ]
Liu Y. [2 ]
Xu X. [1 ]
Chen D. [1 ]
机构：
[1] State Key Laboratory of Aerodynamics, China Aerodynamics Research and Development Center, Mianyang
[2] COMAC Shanghai Aircraft Design and Research Institute, Shanghai
来源：
Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica | 2019年 / 40卷 / 02期
关键词：
Data correction; Model deformation; Support interference; Wall interference; Wide-body aircraft;
D O I：
10.7527/S1000-6893.2018.22205
中图分类号：
学科分类号：
摘要：
Due to its long range and high cruise Mach number, the aerodynamic design of wide-body aircraft requires high precision of its wind tunnel data. To obtain reliable base data of wind tunnel for wide-body aircraft, this paper improves the correction method and related facility in FL-26 wind tunnel of China Aerodynamics Research and Development Center. The test data of high-speed wind tunnel for wide-body aircraft are corrected in several ways, including boundary constrains (support and wall interference), model deformation and flow distortion (flow angle and buoyancy drag). These corrections lay a firm foundation for Reynolds numbers, hydroaeroelasticity and dynamic effect. Results indicate that reliable test results of supporting interference can be obtained by measuring the distribution of the positions of the tail cavity pressure and the length of the false support rod extending into the tail cavity of the model by 50 mm. Within the range of the test envelope, the wall interference has minor influence on the lift, drag and pitch moment coefficients of the wide-body aircraft model. The deformation of the test model significantly influences the aerodynamic characteristics of the wide-body aircraft. After deformation, the lift slope at Mach number=0.85 decreases by 0.005, and the moment focus is moved forward by 0.021 bA. These discrepancies need to be corrected in future tests. © 2019, Press of Chinese Journal of Aeronautics. All right reserved.
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