摘要
本文给出了翼型和机翼跨声速绕流的Galerkin带权余数有限元解法。利用一系列适当形状的元素将计算区域离散,在元素内采用线性插值函数。对于超临界流动,文中采用了适合于有限元法的超声速上风技术,具有捕捉激波的能力。将这种技术应用于线松弛迭代解法中,在计算钝头翼型和机翼绕流时,都获得了成功。
Galerkin finite element method for transonic flow about airfoils and wings is given in this paper. The computational domain is discretized by a series of elements with adaptable shape, linear inter-potation function is used in each element. For supersonic flow, SLOR and an upwind technique suitable to finite element method are employed. The present method is successful in computation of transonic flow about airfoils and wings with blunt nose.
出处
《空气动力学学报》
CSCD
北大核心
1990年第1期76-83,共8页
Acta Aerodynamica Sinica
关键词
机翼
跨声速流
绕流
有限元法
airfoils, wings, transonic flow, finite element.
