北京航空航天大学学报 ›› 1998, Vol. 24 ›› Issue (6): 629-632.

• 论文 • 上一篇    下一篇

三维抛物化N-S方程全隐格式矢通量分裂求解

刘宇, 张振鹏   

  1. 北京航空航天大学 宇航学院
  • 收稿日期:1998-06-09 出版日期:1998-06-30 发布日期:2010-09-29
  • 作者简介:男 35岁 教授 100083 北京
  • 基金资助:

    国家自然科学基金(59786001)和国家高技术"八六三"计划资助项目

Implicit Flux-Vector-Splitting Solution of Three Dimensional Parabolic Navier-Stokes Equations

Liu Yu, Zhang Zhenpeng   

  1. Beijing University of Aeronautics and Astronautics,School of Astronautics
  • Received:1998-06-09 Online:1998-06-30 Published:2010-09-29

摘要: 采用全隐格式的矢通量分裂算法,在通用曲线坐标系内求解三维无因次抛物化强守恒型N-S(Navier-Stokes)方程.所建立的计算程序,可计算较为复杂边界的三维流场,如求解亚、跨、超音速共存的流场,分区模拟内外流共存流动及其混合剪切尾流.给出了一轴对称亚跨超音速喷管内流场的计算结果,包括计算网格,流矢分布,压力、温度和马赫数等值线分布.也给出了一喷管内外流及其混合尾流的计算结果,包括计算网格,流矢分布,无因次压力、密度和温度等值线分布.

Abstract: By the use of implicit flux-vector-splitting method, three-dimensional dimensionless conservative parabolic navier-stokes equation is solved in general curved coordinates system. The code developed can be used to solve the three-dimensional flow field with comparatively complex boundary such as the flow field that subsonic, transonic and supersonic flows appear in it, the flow field that internal and external flows exist together and their mixing wake flow with multi-blocks. An axisymmetric sub-tran-supersonic internal flow field solution of a nozzle is given here including computational grid, flow vector profile, pressure, temperature and Mach number contour line distribution. An inner and outer flow field solution of a nozzle and its mixing wake flow is also presented inside being compose of computational grid, flow vector profile, dimensionless pressure, density and temperature contour line distribution.

中图分类号: 


版权所有 © 《北京航空航天大学学报》编辑部
通讯地址:北京市海淀区学院路37号 北京航空航天大学学报编辑部 邮编:100191 E-mail:jbuaa@buaa.edu.cn
本系统由北京玛格泰克科技发展有限公司设计开发