中文摘要：

利用Fluent软件对基于NACA0018翼型的锯齿尾缘仿生叶片在雷诺数Re=6×105下的三维流场进行了数值模拟,对比研究尾缘锯齿的相对齿高h/λ对叶片气动特性与边界层发展的影响规律。分别选取尾缘锯齿相对高度h/λ为0.5、1.0和1.5,着重分析12°攻角下尾缘锯齿相对高度对仿生叶片近尾缘的涡分布影响。研究表明：当叶片绕流流场出现大尺度分离涡结构时,尾缘锯齿将改变原NACA0018叶片表面流动结构的周期性,对叶片的气动特性产生显著的影响,随相对高度h/λ的增大,仿生叶片的气动性能越接近原始叶片;尾缘锯齿能延迟边界层分离,延迟效果随h/λ的增大而增强;锯齿尾缘能抑制边界层增厚,使叶片尾缘噪声降低。研究12°攻角下的近尾缘涡分布发现,尾缘锯齿间的压力差形成锯齿间的涡和吸力面上的反向旋转涡对,受两者共同影响,叶片近尾缘处的流场分布发生变化,进而影响气动特性。

英文摘要：

The three-dimensional numerical simulation results of NACA0018 airfoil with and without trailing edge（ TE）serrations were presented based on FLUENT when the Reynolds number was 6 × 105,focus on the influence of airfoil aerodynamic characteristics and boundary layer with amplitude of TE serrations h / λ = 0. 5,1. 0 and 1. 5. This work aims to establish a link between the vorticity and amplitude of TE serrations. It was found that the periodical flow field of bionic airfoils with TE serrations were different with NACA0018 airfoil. When the separation area occured largely at the airfoil＇s suction side,the aerodynamic performance of bionic airfoils was negative. And the performance of bionic blade was more similar with higher h / λ. It was found that bionics airfoil with TE serrations could control flow around airfoil,especially the airfoil boundary layer,and boundary layer separation of airfoil with TE serrations was delay and thickness of boundary layer was thinner,and the airfoil self-noise was reduced. Vortex which occurred between the TE serrations would curl around the side edges to the suction side and form a pair of counter-rotating vortices at each sawtooth locally for the pressure difference at TE serrations. Affected by vortex and a pair of counter-rotating vortices,airfoil flow field changed,which could affect aerodynamic characteristics.