针对适用于垂直轴风力机的叶片，以NACA0012作为基准翼型，采用DES湍流模型，在来流雷诺数Re=1×106的情况下进行了等厚度翼型中弧线主动变形运动的数值模拟研究。选用弦长c=0.601 m，展向长度B=1 m，攻角α为15°(浅失速攻角)和18°(深失速攻角)，变形频率f为0.5，2和5 Hz，变形幅值A〖DD(-*2〗-〖DD)〗为0.1c的参数条件，对比变形翼型与不变形翼型的气动性能。研究表明：在深失速攻角下变形翼型相较于不变形翼型，其升力系数提升52%以上，阻力系数减小64%以上，气动性能可得到有效提升，且变形翼型在特定工况下能有效减小翼型表面分离区及分离涡尺度。

Aiming at the blades suitable for vertical axis wind turbine,the NACA0012 was taken as the reference airfoil,the DES turbulence model was adopted to carry out the numerical simulation and research of active deformation movement of mean camber line of airfoils with equal thickness,under the condition of the Reynolds number Re of incoming flow of 1×106.The aerodynamic performances of deformed and undeformed airfoils were compared,under the parameter conditions of the chord length c of 0.601 m,the spanwise length B of 1 m,the attack angle α of 15° (shallow stall angle of attack) and 18° (deep stall angle of attack),the deformation frequency f of 0.5 Hz,2 Hz and 5 Hz,and the deformation amplitude A〖DD(-*2〗-〖DD)〗 of 0.1 c.The research results show that at the deep stall angle of attack,the lift force coefficient of the deformed airfoil is increased by more than 52% and the drag coefficient is reduced by more than 64% compared with those of the undeformed airfoil,and the aerodynamic performance can be effectively improved.Moreover,the deformed airfoil can effectively reduce the surface separation area and the separation vortex size of the airfoil under specific working conditions.

TK83

国家自然科学基金（51406117）；上海市科技启明星计划（19QC1400200）