摘要
采用S-A和RNGK-ε湍流模型对风力机专用S832翼型的绕流流动建立了二维不可压缩湍流模型，利用计算流体力学软件Fluent，对两种模型进行数值模拟，得到了雷诺数为3×10^6时该翼型在-16°～30°攻角下的升力系数和阻力系数与来流攻角的关系以及压力分布图，并进一步分析了不同攻角下翼型表面压力分布特性，预测了大攻角（达30°）下翼型分离流动特性。结合NREL的试验数据，对两种湍流模型模拟的精度进行了分析比较，结果表明在小攻角范围内采用RNGK-~模型预测该翼型气动性，其结果更加有效。
A two-dimensional incompressible turbulence model under S-A, RNCk-ε turbulent models is built for the flow around S832 airfoil, a special-purpose airfoil for HAWTs. The numerical simulation on S832 is acquired by using the CFD software Fluent; the lift and drag coefficients characteristics and pressure distribution are obtained vary with attack angle from --16°to 10° when Re equals 3 × 10^6 ; the separated flow characteristics at large angle of attack （as large as 30 degree ） are predicted after studying the surface pressure distribution characteristics of the airfoil under different angle of attack. The aerodynamic simulation accuracy under these two turbulence models are contrasted through the comparison with NREL＇s aerodynamic data, it is revealed that RNGk-ε turbulence model is more effective in predicting aerodynamic performance of the special-purpose airfoil for HAWTs at small angles of attack.
出处
《能源技术》
2009年第4期219-222,共4页
Energy Technology
关键词
$832翼型
气动性能
分离流
湍流模型
S832 airfoil
aerodynamic performance
separated flow
turbulence model
