风力机翼型大攻角分离流的数值模拟

为了准确预测风力机翼型在大攻角下分离流动的气动性能,并且为风力机的设计与安全运行提供一种可靠的数值模拟手段,针对某风力机专用翼型,分别采用基于非定常不可压缩Navier-Stokes方程的大涡模拟(LES)模型、RNG k-ε模型和Standard k-ε模型对其气动性能进行数值模拟,并计算出翼型攻角为35～90°,雷诺数为2×106时的气动力参数。将不同湍流模型的计算结果与风洞试验数据进行比较,并分析流场结构。分析结果表明,LES模型能够准确地模拟出翼型表面的分离流动,计算结果与试验数据取得了很好的一致性,并且优于RNG k-ε模型和Standard k-ε模型的模拟结果。

The numerical simulation of separated flow at large attack angles for a wind turbine airfoil

In order to accurately predict the aerodynamic performance of the separated flows of a wind turbine airfoil at large attack angles and provide a reliable numerical simulation method for the design and safe operation of the wind turbine,aiming at a certain type of wind turbine airfoil,an aerodynamic performance was numerically simulated by using LES model,RNG k-ε model and Standard k-ε model based on unsteady incompressible Navier-Stokes equations respectively,and the aerodynamic parameters at various attack angles ranging from 35 °to 90 ° was calculated when the Reynolds number is 2×106.By comparing the calculation results of the different turbulence models with wind tunnel test data and analyzing the flow field,it is shown that LES model can accurately simulate the separation of the airfoil surface flows,and its calculated results,which are better than RNG k-ε model’s and Standard k-ε model’s,agree well with the experimental data.