大厚度钝后缘翼型气动性能计算研究

Computational Aerodynamic Analysis of Thick Flatback Airfoils

大厚度钝后缘翼型由于其气动和结构的优点,近来被作为大型风力机叶片设计时的内侧翼型成为风力机翼型设计的热点之一EULL由于此类翼型厚度和风洞阻塞度的限制,大雷诺数的风洞实验数据很少。耦合RANS方程和基于线性稳定性分析EULL捩预测方法,进行了大厚度钝后缘翼型气动性能计算研究。使用Gridgen程序生成计算网格,湍流模型为S-A模型。对常用的钝后缘修形方式如直接截断、对称增加厚度等并且有风洞实验结果的几种翼型进行了CFD计算并和实验结果及文献计算结果进行了比较。结果表明升力系数在线性段,计算结果和实验结果吻合很好,但是对失速迎角的捕捉能力差;阻力系数计算结果和实验值吻合较好。不同修形方式的计算结果为钝后缘修形设计提供了参考。

Flatbact（blunt trailing edge） airfoils are adopted for the inboard region of large wind turbine blades due to their structural and aerodynamic performance advantages.But very limited experimental data at high Reynolds Numbers are available because the wind tunnel experiments are limited by the Reynolds Number and solid blockage.In this study,a 2-D Reynolds-Averaged Navier-Stokes solver coupled with a transition prediction based on eN method is used to CFD calculated of blunt trailing edge airfoils.Several blunt trailing edge airfoils,blunting the trailing edge by different methods and with experimental data,are calculated and the results are analyzed.The results show that the CFD results of lift coefficients agree very well in linear region with the experimental data but the maximum lift is over predicted and post-stall phenomena are not captured computationally.