摘要
从全速位方程出发研究了机翼和翼身融合体跨音速绕流的有限元算法。给出适用于有限元法和复杂外形的块结构网格生成技术和使单元系数矩阵积分数目减少2/3的方法;并发展了一种内存量少的总体系数矩阵存贮方式。为了提高有限元离散方程组解的精度和加速收敛,提出α—GMRES算法代替传统全速位方程有限元解法中所习用收敛慢的线松弛迭代解法。通过机翼和翼身融合体实例考核,效果是好的,为飞行器先进气动布局的数值计算提供了一种新的有效算法。
The finite element algorithm for transonic flows about wing and blended wing-body configuration is investigated based on the full potential equations. The blocked structured mesh generation technigue, which is suitable for finite element method and complex configuration, and the method for reducing the number of integrals of the element matrix are given. A new compact storage scheme for the global matrix is also developed. In order to improve the accuracy of the solution of the discretized coupled equations resulting from the finite element method, an α-GMRES algorithm is proposed to replace the traditional iterative line relaxation method used in the finite element algorithm for solving the full potential equations. Several concrete numerical examples for wing and blended wing-body configuration show that the present method is efficient and provides a new effective algorithm for the numerical analysis of the advanced aerodynamic layout of aircraft.
出处
《航空学报》
EI
CAS
CSCD
北大核心
1992年第12期B579-B585,共7页
Acta Aeronautica et Astronautica Sinica
关键词
有限元法
跨音速流动
翼身
机翼
finite element method, transonic flows, blended wing-body configuration, wings
