雷诺数对低速对称翼型气动性能的影响

Effects of Reynolds Number on Low Speed Symmetrical Airfoil Aerodynamic Performance

基于CFD软件,采用k-ω SST湍流模型,研究了不同雷诺数对低速对称翼型NACA0012、NACA0015和NACA0018气动性能的影响,以及同一雷诺数下翼型相对厚度对翼型气动性能的影响。比较了翼型NACA0012、NACA0015和NACA0018的升力系数和阻力系数的计算值与试验值,得出了和试验值最接近的翼型,总结了对称翼型升力系数、阻力系数和升阻比的变化规律,确定了对称翼型最佳攻角。结果显示,低速对称翼型相对厚度越大,气动性能越好;雷诺数越小,黏性越大,越先发生边界层分离;翼型NACA0018的计算值和试验值最接近;翼型NACA0018的最佳攻角为10°。

The paper researched the effects of different Reynolds number on low speed symmetrical airfoil aerodynamic performance including NACA0012, NACA0015 and NACA0018 based on CFD software and by taking k-ω SST turbulence model, at the same time, the effects of airfoil relative thickness on the low speed symmetrical airfoil aerodynamic perform- ance with the same Reynolds number have been researched and compared calculated value and experimental value of lift coef- ficient and drag coefficient of the airfoil NACA0012, NACA0015 and NACA0018, got the closest airfoil with the experimen- tal values. Summarized the change rule of lift coefficient, drag coefficient and lift-drag ratio, and determined the best angle of the airfoil. The results showed that the bigger the relative thickness of the low speed symmetrical airfoil is, the better aerodynamic performance is, the smaller of Reynolds number is, the bigger of viscosity is, the more easily boundary-layer separation occurs, the closest of calculated value of the airfoil NACA0018 to experimental value is. The best angle of the airfoil NACA0018 is 10 degree.