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以具有实验数据的风力机专用翼型DU97-W-300、DU00-W2-401为对象,研究了湍流模型和网格分布对RANS预测气动性能的影响,并在多个攻角下对比了DES与RANS的计算效果.结果表明:在翼型升力曲线的线性段,考虑转捩的T-SST模型计算值与实验值更加吻合,但在升力曲线的失速段,全湍流模型计算结果优于T-SST湍流模型,且全湍流模型中SA优于SST湍流模型;相比RANS方法,DES方法计算得到的翼型升阻力系数更加接近实验值,DES方法能更好地模拟细致的分离涡结构,所以DES方法更加适合模拟易发生分离的大厚度翼型.
Taking the airfoil DU97-W-300 and DU00-W2-401 as experimental data, the effects of turbulence model and grid distribution on the aerodynamic performance of RANS are studied and the effects of DES The results show that the calculated results of T-SST model agree well with the experimental values in the linear section of lift curve of airfoil, but the results of turbulence model are better than T -SST turbulence model, and the SA is better than the SST turbulence model in the full turbulence model; compared with the RANS method, the lift coefficient of lift calculated by DES method is closer to the experimental value, DES method can better simulate the detailed separation of vortex structure, Therefore, the DES method is more suitable for simulation of large-thickness airfoils prone to separation.