摘要
在Re=3×106下,基于k-w SST两方程湍流模型对两种不同厚度的NREL风力机专用翼型进行了数值模拟,重点研究了-5°～15°攻角下不同厚度对翼型气动特性的影响规律。非定常计算结果表明:不同厚度对翼型气动性能影响显著,在某一小攻角范围,较小厚度值可获得较大升阻比,在大攻角翼型发生失速时,较大厚度值可提高翼型的升阻比,拓宽高升阻比的攻角范围,有效改善翼型的分离流动特性。
Based on the k-w SST turbulence model , two airfoils of different thickness are simulated at Re = 3 × 10^6, the aerody- namic characteristics of airfoil with different thicknesses at the attack angle of -5°- 15° are investigated. The unsteady numerical results show that ：the effect of the different aerofoil thickness is obvious to the aerodynamic performance , at a small angle of attack range , the greater thickness leads to the large lift-drag ratio , at large angle of attack ,larger thickness can improve the liftdrag ratio, broaden the scope of the angle of attack of the high lift-drag ratio , effectively improve the flow separation characteristics.
出处
《流体机械》
CSCD
北大核心
2010年第2期31-34,共4页
Fluid Machinery
