Aeroelastic analysis of rotor airfoil based on CFD/CSD tight coupling method

被引：0
|
作者：
Huang D.-B. [1 ]
Li J.-D. [2 ]
Liu Y. [1 ]
机构：
[1] National Key Laboratory of Science and Technology on Rotorcraft Aeromechanics, Nanjing University of Aeronautics and Astronautics, Nanjing
[2] Xi'an Advanced Dynamics Technology Incorporation, Xi'an
来源：
Liu, Yong (liuyong@nuaa.edu.cn) | 1820年 / Beijing University of Aeronautics and Astronautics (BUAA)卷 / 31期
关键词：
Aerodynamic load; Airfoil; Blade; CFD/CSD tight coupling; Helicopter; Structural response;
D O I：
10.13224/j.cnki.jasp.2016.08.004
中图分类号：
学科分类号：
摘要：
By coupling the calculation of the unsteady aeroforce and the vibration response through the development of CFD/CSD (computational fluid dynamics/computational structure dynamics) tight coupling method, the Fluent code was calculated, and the data of structural response and dynamic load were exchanged by UDF (user defined function)and reading and writing the I/O (input/output) files. The aerodynamic characteristics and vibration response of the airfoil at the condition of pitching motion, plunging (flapping) motion and periodic alternating incoming flow were studied. Numerical results indicated that the aerodynamic load was periodic, showing a smoothing hysteresis curve in rotating process, and the flapping responses also showed a cyclical phenomenon, the pitching response showed slight oscillation at slight stall condition. At the deep stall condition, the aerodynamic load or structural response showed strong nonlinear oscillation, high frequency components were more obvious. © 2016, Editorial Department of Journal of Aerospace Power. All right reserved.
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页码：1820 / 1829
页数：9
相关论文
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