风力机翼型等速上仰动态失速数值模拟

采用κ-ωSST模型，利用CFD软件模拟了NREL S809翼型正弦振荡动态失速，并将结果和俄亥俄州立大学（OSU）风洞试验值对比，显示出较好的一致性，验证了所用方法的有效性．在此基础上对该翼型在雷诺数Re=1．0×10^6时以攻角变化率α=34．54（＊）·s^-1等速上仰动态失速过程进行了数值模拟，详细描述了等速上仰动态失速过程涡的发展以及翼型周围流场的分布．结果表明，动态失速现象是由前缘主涡和尾缘逆向涡交替作用引起；其气动特性曲线的分析结果表明，其失速前气动性能较静态时有较大提升．

Numerical simulation of identical pitching wind turbine airfoil dynamic stall

The dynamic stall aerodynamic characteristics of S809 airfoil undergoing sinusoidal oscillations was investigated by the SST turbulence model of CFD solution. The simulation results were compared with the OSU wind-tunnel test data, which showed a good agreement and validated the effectiveness of the used methods. Based on this, the dynamic stall process of identical pitching of S809 airfoil at Re = 1.0 × 10^6 and the change rate of angle of attack α = 34.54 （＊） · s^-1 was simulated,and the development of vortices and flow field distributions were presented in detail. The simulation results showed that the phenomenon of dynamic stall was aroused by leading edge vortices and training edge vortices. In addition, the aerodynamic characteristic curves were analyzed and the aerodynamic characteristic was an increase compared with that of steady condition.