Test on active control of airfoil dynamic stall based on trailing edge flap

被引：0
|
作者：
Li G. [1 ,2 ]
Song K. [2 ]
Qin C. [2 ]
Zhao G. [2 ]
Wu L. [2 ]
Yang Y. [2 ]
机构：
[1] College of Aerospace Science and Engineering, National University of Defense Technology, Changsha
[2] Low Speed Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang
来源：
Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica | 2024年 / 45卷 / 03期
关键词：
aerodynamic damping; dynamic stall; rotor; stall flutter; trailing edge flap;
D O I：
10.7527/S1000-6893.2023.28699
中图分类号：
学科分类号：
摘要：
Aiming at the increase of unsteady load and stall flutter caused by dynamic stall，test research focusing on the control of airfoil dynamic was carried out using an airfoil test model with trailing edge flaps. The test Reynolds num⁃ ber was Re = 7. 0 × 105，and the reduced frequency k = 0. 097. Dynamic pressure measurement was used to analyze the influence of different oscillating phase offsets，amplitudes and equilibrium angles of attack of the trailing edge flap on the airfoil during dynamic stall. The results show that the trailing edge flap with continuous sinusoidal oscillation can alternately change the aerodynamic performance of the airfoil with the time interval of 1/2 of the oscillation period. When the phase offset between the trailing edge flap and airfoil model is 0°，the peak pitching moment can reduce by 54. 9% and a larger oscillation amplitude of the trailing edge flap seems to achieve a better control effect of unsteady load，but stall flutter may appear when it is too large. The oscillation equilibrium angle of attack of the trailing edge flap can change the lift coefficient and aerodynamic damping. © 2024 Chinese Society of Astronautics. All rights reserved.
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  • [1] LEISHMAN J G., Principles of helicopter aerodynamics ［M］, (2006)
  • [2] YANG H S, ZHAO G Y，, LIANG H, Et al., Research progress on influence factors of airfoil dynamic stall and flow control［J］, Acta Aeronautica et Astronautica Sinica, 41, 8, (2020)
  • [3] WANG Q., Study on dynamic stall mechanism and aerodynamic shape optimization of rotor［D］, pp. 61-72, (2017)
  • [4] ZHAO Q J，, WANG Q, ZHAO G Q., New optimization design method for rotor airfoil considering steady-unsteady characteristics［J］, Journal of Nanjing University of Aeronautics & Astronautics, 46, 3, pp. 355-363, (2014)
  • [5] WANG Q, ZHAO Q J, WU Q., Aerodynamic shape optimization for alleviating dynamic stall characteristics of helicopter rotor airfoil［J］, Chinese Journal of Aeronautics, 28, 2, pp. 346-356, (2015)
  • [6] YU B P, XIE L, Et al., Dynamic stall optimization design of rotor airfoil based on surrogate model［J］, Journal of Zhejiang University（Engineering Science, 54, 4, pp. 833-842, (2020)
  • [7] ZHAO Q J, JING S M，, ZHAO G Q，, Et al., Review of research progress on dynamic stall mechanism and unsteady design of rotor airfoils［J］, Acta Aerodynamica Sinica, 39, 6, pp. 70-84, (2021)
  • [8] ZHANG X，, HUANG Y, WANG X N，, Et al., Flow control on a supercritical wing using dielectric barrier discharge plasma actuator［J］, Acta Aeronautica et Astronautica Sinica, 37, 6, pp. 1733-1742, (2016)
  • [9] LI Z, ZHANG J，, Et al., Reverse jet control of high-speed flow field in plasma synthetic jet actuator［J］, Acta Aeronautica et Astronautica Sinica, 43, pp. 228-235, (2022)
  • [10] MA Z X, LUO Z B, ZHAO A H, Et al., Reverse jet characteristics of plasma synthetic jet in hypersonic flow field ［J］, Acta Aeronautica et Astronautica Sinica, 43, pp. 195-206, (2022)
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