摘要
本文将Ｄｅｌａｕｎａｙ法用于复杂物形的非结构网格生成，并利用黄明恪提出的布点原理避免边界穿透。绕流的计算采用Ｅｕｌｅｒ方程和Ｊａｍｅｓｏｎ的有限体积法。本文对三维问题提出新的激波敏感器，对方法做了改进，并用于ＡＧＡＲＤＭ６机翼、导弹模型和飞机模型的绕流计算。
In this paper,the Delaunay triangulations is used to generate the unstructured mesh for three dimesional configurations.To avoid the boundary breakthroughs,a principal of the proper location of the node points is proposed.To compute the flow past the configuration by Euler equations and Jameson’s finite volume method,a new shock sensor is suggested for improvement.The proposed method is applied to compute the compressible flows past the AGARD M 6 wing, a missile and aircraft models.
出处
《空气动力学学报》
CSCD
北大核心
1999年第1期15-20,共6页
Acta Aerodynamica Sinica
基金
国家航空科学基金
