Effect of bionic sinusoidal leading-edge on dynamic stall of airfoil

被引：0
|
作者：
Hou Y. [1 ,2 ]
Li Z. [1 ,2 ,3 ]
机构：
[1] School of Energy and Power Engineering, Beihang University, Beijing
[2] National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics, Beihang University, Beijing
[3] Beihang (Sichuan) West International Innovation Port Technology Co., Ltd., Chengdu
来源：
Li, Zhiping (LeeZIP@buaa.edu.cn) | 1600年 / Chinese Society of Astronautics卷 / 41期
关键词：
Dynamic stall; Load peaks; Passive control; Separation vortex; Sinusoidal leading-edge;
D O I：
10.7527/S1000-6893.2019.23276
中图分类号：
学科分类号：
摘要：
Dynamic stall causes dramatic changes in aerodynamic loads of blades, leading to a sharp increase in vibration loads and a significant decrease in blade life. To solve the dynamic stall problem of airfoil, this paper obtains inspiration from the good flow characteristics of humpback whale's pectoral fins under dynamic tilt, and models the bionic sinusoidal leading-edge airfoil (including three peaks and two wavelengths) to suppress dynamic stall. With the help of three-dimensional unsteady numerical simulation method, the control mechanism of bionic leading-edge on dynamic stall and the effects of motion parameters and inflow velocity on SC1095 rotor airfoil are studied by using the moving grid technology. The results show that the peak values of pitch moment coefficient and drag coefficient are reduced greatly by sinusoidal leading-edge. The bigger the wave peak and the smaller the wavelength of the leading-edge, the more obvious the suppression effect of the peak values of drag coefficient and pitch moment coefficient are. Although the peak value of lift coefficient decreases, the reduction is much smaller than that of the former two. For example, for one of the bionic wings, the peak pitch moment coefficient decreases by 47.7%, the peak drag coefficient decreases by 36.4%, whereas the peak lift coefficient decreases by 14.1%. At approximately the maximum angle of attack, the sinusoidal leading-edge can mitigate stall characteristics and make the load change more gently. At higher average angle of attack, low pitch frequency and low Mach number, the dynamic stall control effect of bionic wing is stronger. Comparatively speaking, amplitude of angle of attack matters less. © 2020, Press of Chinese Journal of Aeronautics. All right reserved.
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