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本文以NACA0012翼型为研究对象,采用混合网格划分方法和SST κ-ω湍流模型,数值模拟了雷诺数Re=2.7×10~5条件下减缩频率和平均攻角对翼型俯仰振荡气动特性的影响。结果表明:翼型俯仰运动时的平均升力系数均低于静态条件下的升力系数;减缩频率对翼型下行段气动特性影响最为显著,当减缩频率较小时,翼型刚开始下行运动,出现流动分离越显著,这导致平均升力系数与静态条件下升力系数差值变大;平均攻角越大,俯仰运动时的最大升力系数越小;翼型俯仰运动上行段升力系数大,主要是因为前缘流动加速剧烈,增大了上下表面压差。
In this paper, the NACA0012 airfoil is used as the research object. The mixed meshing method and the SST κ-ω turbulence model are used to numerically simulate the aerodynamic characteristics of the airfoil’s pitch oscillation with the decreasing frequency and the average angle of attack under the Re = 2.7 × 10 ~ 5 Reynolds number Impact. The results show that the average lift coefficient of airfoil during pitching is lower than that under static condition. The effect of shrinkage frequency on the aerodynamic characteristics of airfoil downstream is the most significant. When the frequency of shrinkage is small, the airfoil begins to descend and flows The more significant the separation, which led to the difference between the average lift coefficient and the lift coefficient under static conditions. The larger the average angle of attack, the smaller the maximum lift coefficient during pitch movement. The larger the lift coefficient, Edge flow accelerated, increasing the upper and lower surface pressure.