摘要
发展了一种快速抛物型方程贴体及与边界正交网格生成技术。生成了某歼击机全机真实外形三维Ｏ－Ｃ型计算网格，并应用于跨音速流场欧拉方程数值计算。成功地模拟了绕全机的复杂流场。计算压力分布与实验吻合良好。
A Fast grid generation procedure named parabolic equation method for complex aircraft is developed. Grid is obtained by marching from body surface to outer boundary. Successful control of grid orthogonality on body is achieved by means of the introduction of algebraic grid prediction. A numerical algorithm based on a finite volume explicit scheme is employed for calculating transonic flow around a realistic aircraft configuration. Comparisons of the computational results with experimental data show very good agreement in terms of trends.
出处
《计算物理》
CSCD
北大核心
1998年第2期45-50,共6页
Chinese Journal of Computational Physics
基金
航空基金
航空高等院校自选科研课题
