摘要
在全三元流动计算获得了叶片表面速度分布的基础上，对一台０．８０ｍ直径的轴流式通风机进行了叶片表面层流边界层求解．首先用积分方法导出了适用于计算机解的层流边界层微分方程，然后进行了计算并获得了所有层流段边界层的物理参数．该项研究成果为边界层的控制和叶片优化，以及风机损失计算和效率的提高提供了依据．
Based on the results of full 3D flow field calculating and obtaining blade surface velocity distributions ,laminar boundary layer on blade surfaces of a 0.8 meters diameter axial fan was calculated.Firwt,differential equations suitable for computing on a computer was brought about by means of integral.Then its laminar bundary layer was calculated and the whole physical parameters were obyained.Theachievements of the research provides basis for blade design,blade optimization,axial fan loss calculationand bloundary layer control.
