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.

引用

共 25 条

[11] KHALIL K，, ASARO S，, BAUKNECHT A., Active flow control devices for wing load alleviation［J］, Journal of Aircraft, 59, 2, pp. 458-473, (2021)
[12] DE VRIES, Et al., Fluidic load control for wind turbine blades, 47th AIAA Aerospace Sciences Meeting including The New Horizons Forum and Aerospace Exposition, (2009)
[13] WANG H F，, DENG F，, LIU X Q，, Et al., Gust load alleviation control based on jets for natural laminar airfoil ［J］, Acta Aeronautica et Astronautica Sinica, 43, 11, (2022)
[14] BAUKNECHT A., Coandă -type flow actuation for load alleviation［J］, Journal of Aircraft, 59, 5, pp. 1303-1319, (2022)
[15] QIN N., Airfoil gust load alleviation by circulation control［J］, Aerospace Science and Technology, 98, (2020)
[16] QIN N., Gust load alleviation on an aircraft wing by trailing edge Circulation Control［J］, Journal of Fluids and Structures, 107, (2021)
[17] SMITH D R，, WARSOP C., NATO AVT-239 task group：‘innovative control effectors for manoeuvring of air vehicles’‐introduction and overview［C］∥ AIAA Sci-tech 2019 Forum, (2019)
[18] SMITH B L，, GLEZER A., The formation and evolution of synthetic jets［J］, Physics of Fluids, 10, 9, pp. 2281-2297, (1998)
[19] AMITAY M., Synthetic jets［J］, Annual Review of Fluid Mechanics, 34, 1, pp. 503-529, (2002)
[20] ZHU X P，, ZHOU Z，, Et al., Application of active flow control technique for gust load alleviation［J］, Chinese Journal of Aeronautics, 24, 4, pp. 410-416, (2011)

← 1 2 3 →