尾缘加厚翼型的三维旋转特性研究

Study on 3D rotation characteristics of trailing edge enlarged airfoils

采用计算流体动力学(CFD)方法对MEXICO试验风力机叶片不同部位翼型在旋转状态下的升阻力系数进行计算,并与试验数据进行比较分析,验证了CFD方法能够准确预测翼型在旋转状态下的升阻力系数。通过采用尾缘对称加厚到5%翼型弦长的DU 97-W-300-05翼型和对应的尾缘未加厚的DU 97-W-300翼型设计,得到沿叶片径向具有相同弦长的风力机叶片,并采用CFD方法对该叶片在旋转状态下的气动特性进行计算。结果表明:在旋转状态下,当攻角小于15°时,尾缘加厚翼型的升力系数比相对应的尾缘未加厚翼型大10%左右;尾缘加厚翼型在旋转状态下的粗糙度敏感性好于相对应的尾缘未加厚翼型;随半径增大,尾缘加厚翼型和对应的尾缘未加厚翼型的升力系数都增大,但失速提前,尾缘加厚翼型升力系数增大得更明显。

In this paper, Computational Fluid Dynamics（CFD） method was employed to predict the lift and drag coefficients of airfoils at different radii of MEXICO（Model EXperiments In Controlled c Onditions） experimental wind turbine, the computational results were compared with experimental results to validate the prediction accuracy of CFD, the results show that CFD can predict the lift and drag coefficients of airfoils under rotating conditions accurately. Then, CFD method was used to predict the aerodynamic characteristics of a rotor which is newly designed with trailing edge enlarged airfoil and the same chord length along the radial direction, so the characteristics of trailing edge enlarged airfoil under rotating conditions can be obtained which show that the lift coefficients of trailing edge enlarged airfoil is 10 percent larger than that of respectively original airfoil below an angle of attack of 15 degrees. What＇s more, the roughness sensitivity of trailing edge enlarged airfoil is better than that of respectively original airfoil under rotating conditions. At last, with the increase of radius, the lift coefficients of trailing edge enlarged and original airfoils both increase but stall occurs ahead, the increment of lift coefficients of trailing edge enlarged airfoil is larger than that of respectively original airfoil under rotating conditions.