跨音速叶栅边界层计算  

Calculation of Transonic Boundary Layer

作　　者：李淑英 郑洪涛 刘顺隆 

机构地区：[1]哈尔滨工程大学船舶动力工程系,哈尔滨150001

出　　处：《哈尔滨工程大学学报》1996年第2期6-12,共7页Journal of Harbin Engineering University

摘　　要：分别应用微分法和积分法对适于跨音速流进行了剪切边界展计算。在微分法中,以 Cebeci-Smith 方法为基础,沿流动方向采用加权六点格式作了适当改进;并且用驻点方程的相似性解确定了前驻点速度分布的边值条件,避免了边界层方程在驻点邻域的困难,同时对不同形式的驻点方程的求解结果对边界层计算的影响进行了比较和讨论。利用动量积分对任意旋成面叶栅进行了湍流边界层计算,并与微分法计算进行了比较和讨论。In this paper, both numerical differentiation and integration methods are adopted to tran- sonic turbulent boundary layer flow problem. In differentiation method. Cebesi-Smith's tech- nique is modified with 6 point weighted scheme, along the flow direction. And the similarity solution of stagration equation is used to determine the boundary condition for the velosity dis- tribution near the stagnation point, overcoming the difficulty of imposing boundary condition there. In addition, the effects of different stagnation equations on boundary layer calculation result are compared and discussed. Turbulent boundary layer is calculated by use of momentum integration for cascade of arbitrary stream surface of revolution. The results from differentiation and integration methods are discussed, and compared with each other.

关 键 词：边界层 微分法 积分法 跨音速流 叶栅 

分 类 号：O354.2[理学—流体力学]