Airfoil gust load alleviation based on dual synthetic jets

被引：0
作者：
Wang, Hao [1 ]
Luo, Zhenbing [1 ]
Deng, Xiong [1 ]
Zhou, Yan [1 ]
Zhang, Jianyuan [1 ]
Zhao, Zhijie [1 ]
机构：
[1] College of Aerospace Science and Engineering, National University of Defense Technology, Changsha
来源：
Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica | 2024年 / 45卷 / 16期
基金：
中国国家自然科学基金;
关键词：
dual synthetic jets; gust alleviation; reverse jet; separated vortex; vortex shedding;
D O I：
10.7527/S1000-6893.2023.29660
中图分类号：
学科分类号：
摘要：
To study the gust alleviation strategy based on Dual Synthetic Jets（DSJ），we arrange the actuators in an array on the upper surface of the NACA0012 airfoil，actively induce the flow separation through reverse jets，and study the evolution of the separated vortex and the dynamic vortex shedding，providing a new insight for load control based on the zero-mass jet. The results show that with the increase of the momentum coefficient Cμ，the control ability of DSJ over the gust load is gradually improved without causing large fluctuation of the lift coefficient CL. At Cμ = 0. 033，the trailing edge separation zone develops to the middle position of the airfoil，and the response amplitudes of CL，max decrease by 47. 9%. Because of the large separation zone at the trailing edge，the unloading process of the separated vortex on the upper wing surface after closing the jet actuator will have a significant impact on CL. In the process of airflow impacting the separated vortex，the pressure difference between the upper and lower wings rapidly increases，leading to rapid decrease of CL. Then，aiming at this process，we study the Cμ step-decreasing control，and set the Cμ interval change. Compared with the case of continuously applying constant Cμ，this control method requires less energy consumption in achieving the same slowing amplitude，and the airfoil also spends less time under high load impact. © 2024 Chinese Society of Astronautics. All rights reserved.
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