在这项研究中CFD分析的二维流将分0012翼型进行使用ANSYS流利的和对实验数据结果进行比较。不可压缩流在机翼进行2 d C类型分析。影响网格和数值方法研究了6 o的角度攻击。压力,速度升力和阻力系数与不同的仿真网格相比,它显示了最大网格接近100000点有6%的变化提升计算及阻力计算21%的变异。网的使用偏误类型和因素是精制接近机翼获得准确的结果。然而捕捉粘性影响细孔网是必需的,因为附近墙上流切向速度的迅速变化,Fig.5.1所示。这需要仔细的描述计算网格墙附近一个非常细网格正常在墙上。这个改进强烈影响计算壁摩擦。
In this study CFD analysis of the 2-D flow over the NACA 0012 airfoil profile are performed using ANSYS Fluent and results are compared against the experimental data. The incompressible flow over the airfoil is performed in a C Type 2D analysis. Influence of the Mesh and the numerical method have been studied for 6o the angle of attack. Pressure, velocity lift and drag coefficients are compared with different mesh of the simulation, it shows the Maximum mesh close to 100,000 points gives 6 % variation in lift calculation and 21 % variation in drag calculation. Using bias type and factor the mesh is refined close to airfoil to get the accurate results. However for capturing viscous effect finer mesh is required because Near the wall the tangential velocities in the flow rapidly change as shown in Fig.5.1. This demands a careful description of the computational grid near the wall with a very fine grid normal to the wall. This refinement strongly influences the computed wall friction.