翼型和叶栅前后缘局部流场的新精化解法

本文提出一种利用前后驻点自动定位来求前后缘局部流场精化解的方法 ,即在全流场解的基础上 ,把局部流场解分为两部分的叠加 ,其中之一是驻点邻区的近似解析解 ,它吸收了原解中变化急剧的部分 ,使剩余部分成为变化比较平缓、具有更好的解析性态的分布 ,因而易于求准确。算例表明 ,本文方法为提高亚声绕统计算精度 ,特别是带攻角绕流工况 ,提供了有效的手段 ,本文思想也可同变分差分法结合应用

A NEW METHOD FOR SOLVING LOCAL FLOW NEAR LEADING OR TRAILING EDGE OF AN AIRFOIL

a new algorithm coupled with the variational finite element method (FEM) is presented for solving the local flow near the leading or trailing edge of an airfoil or cascade.The solution of the local flow is considered as a combination of two parts.One of them is the approximate analytical solution of the flow near the stagnation point,it absorbs the greatly changing part in the original solution and makes the rest a more smooth distribution with better analytical nature which can be computed more accurately.Taking advantage of the variational principles,it is possible to locate the stagnation point more precisely and automatically.The numerical results show that the method described is effective to solve the subsonic flow accurately,especially in conditions with non-zero angle of attack.The theory can be coupled with the variational difference method as well as the variational FEM.