基于RANS方程大型风力机翼型钝尾缘修型气动性能计算  

AERODYNAMICS PERFORMANCE COMPUTATIONAL OF TRAILING-EDGE-BLUNTING METHODS OF FLATBACK AIRFOIL FOR LARGE WIND TURBINE BASED ON RANS EQUATION

作　　者：邓磊[1] 乔志德[1] 杨旭东[1] 熊俊涛 

机构地区：[1]西北工业大学翼型叶栅空气动力学国家级重点实验室,西安710072 [2]加州大学欧文分校机械与航空与太空工程系,美国加州欧文ca926973975

出　　处：《太阳能学报》2012年第4期545-551,共7页Acta Energiae Solaris Sinica

基　　金：国家高技术研究发展(863)计划(2007AA05Z448)

摘　　要：通过耦合求解二维定常RANS方程和基于线性稳定性分析的转捩预测程序,计算了DU97-Flat翼型的气动性能并与实验结果进行比较,结果表明该文方法可进行有钝尾缘厚度翼型的气动性能计算。使用耦合求解方法,以DU97-W-300翼型为例,计算几种常见的风力机翼型钝尾缘修型方法(直接截断、对称加厚、不对称加厚和翼面旋转等)得到的钝尾缘翼型的气动性能,并分析各种修型方法对气动性能的影响。结果表明:直接截断修型方法并未增加此翼型的升力系数但对阻力增加的影响最小;不对称增加厚度引起的升力系数增加最明显,但会引起翼型使用角度区域的移动;通过指数因子形式对称增加时,指数因子在1.8～2.5之间较适中。The aerodynamic performance of a flatback airfoil of DU97-Flat was calculated by solving 2-D ReynoldsAveraged Navier-Stokes equations coupled with a transition prediction code based on eN method and compared with experimental results. The results show that the CFD method in present study can be used to calculate the aerody- namic performance of flatback airfoils. The DU97-W-300 airfoil was used as a base-foil to design flatback airfoils by several design methods （ ie. Truncation, adding trailing edge thickness symmetrically and dissymmetrically, and ro- tating curves of airfoil）. The designed flatback airfoils were calculated and the effects of different design methods on aerodynamic performance were analyzed. The results show that the flatback airfoils designed by truncation do not lead to an increase in lift coefficient in present case; adding trailing edge thickness dissymmetrically leads to a most significant increase in lift coefficient and a move of working angle-of-attack ; the power factor should be 1.8 - 2.5 if adding trailing edge thickness symmetrically with a power function.

关 键 词：风力机 翼型 钝尾缘 气动性能 eN方法 

分 类 号：V211.412[航空宇航科学与技术—航空宇航推进理论与工程]