摘要
以势流理论为基础,采用工程方法并参考试验结果确定分离涡的起始分离位置,用不可压流涡段所产生扰动流场的线性迭加,计算涡分离流动流场。单独翼面、组合翼面标模和FC-1飞机计算结果与实验结果的对比表明,在失速迎角范围内,本文方法是一种有效的低速大迎角气动特性快速计算方法。
Based on the potential theory, a linearity combination of the disturbance flow field generated by the uncom-pressible vortex part was applied in the computation of separate vortex flow. As the computation of single wing-surface, combined wing-surfaces and FC-1 aircraft showed, this low speed and high AOA aerodynamic computing method given in this paper is effective in the range of stall AOA.
出处
《空气动力学学报》
CSCD
北大核心
2007年第4期541-545,共5页
Acta Aerodynamica Sinica
关键词
大迎角
势流
分离流
非线性
AOA
potential flow
separated flow
nonlinear
