通用风力机翼型气动特性数值模拟

Numerical Simulation on Aerodynamic Performance of General Airfoil

针对某翼型扰流流动,建立了二维可压缩湍流模型,利用商业软件FLUENT对翼型不同来流攻角下的气动特性进行了相应的数值模拟计算.湍流黏度采用基于RANS的Spalart-A llm aras湍流模型处理,得出了雷诺数在3.2×106时,某翼型的升力系数、阻力系数和压力分布随来流攻角的变化关系,并与同类翼型实验数据进行对比.结果显示:该翼型与修型前的翼型相比,具有较高的升力系数和升阻比,失速性能更好.

2D physical and mathematical model is built to simulate the flow around an airfoil, the steady compressible Reynolds-Averaged Navier-Stokes equations are solved numerically and SpalartAllmaras turbulence model is applied to solve the turbulent viscosity using the CFD commercial software called FLUENT. The coefficients of lift and drag as well as the pressure distribution are concluded with the change of angle of flow attack for airfoil at Reynolds number of 3.2e ＋ 06. The comparison between computed results and similar airfoil＇ experimental data show that results using Spalart-Allmaras turbulence model are closer to experimental results, and the airfoil has higher lift coefficient and higher lift-drag ratio.