Advanced Search
Volume 24 Issue 6
Jun.  1998
Turn off MathJax
Article Contents
Journal of Beijing University of Aeronautics and Astronautics  > 1998  >  24(6): 671-675.
Cai Guobiao, Zhang Huazhao, Zhuang Fengganet al. Numerical Simulation of Chemical Reacting Flow in H2/O2 Rocket Engine Thrust Chamber[J]. Journal of Beijing University of Aeronautics and Astronautics, 1998, 24(6): 671-675. (in Chinese)
Citation: Cai Guobiao, Zhang Huazhao, Zhuang Fengganet al. Numerical Simulation of Chemical Reacting Flow in H2/O2 Rocket Engine Thrust Chamber[J]. Journal of Beijing University of Aeronautics and Astronautics, 1998, 24(6): 671-675. (in Chinese)
shu

Numerical Simulation of Chemical Reacting Flow in H2/O2 Rocket Engine Thrust Chamber

  • 1.

    Beijing University of Aeronautics and Astronautics,School of Astronautics

  • 2. Beijing Institute of Space System Engineering

  • 3. Beijing University of Aeronautics and Astronautics,Dept. of Flight Vehicle Design and Applied Mechanics

  • Received Date: 09 Apr 1998
  • Publish Date: 30 Jun 1998
    Abstract
  • The viscous chemical reacting flow in the hydrogen-oxygen rocket engine chamber and nozzle is simulated by using loosely coupled point-implicit MacCormack scheme. In the numerical simulation the combustion process is modeled by using a 6-specis, 8-step finite-rate chemical reaction model, and the Baldwin-Lomax algebraic turbulent model is adopted. The distributions of flow parameters in the chamber and nozzle are presented. Analysis of the results show that the numerical simulation results are the same as the distributions of flow parameters in the hydrogen-oxygen rocket engine chamber and nozzle, so the result is proved to be reliable. The work of this paper lays a foundation for the numerical simulation of two-phase chemical reacting flow.

     

    • FullText(HTML)
  • loading
    • References(1)
  • 1. Evans J S,Schexnayder C J. Critical influence of finite rate chemistry and unmixdness on ignition and combustion of supersonic H2-air streams. AIAA Paper 79-0355,1979 2. Drummond J P,Rongers R C,Hussaini M Y.A detail numerical model of a supersonic reacting mixing layer.AIAA Paper 86-1427,1986 3. Imlay S,Eberhardt S.A diagonal implicit scheme for computing flow with finite-rate chemistry.AIAA Paper 90-1577,1990 4. 刘国球,任汉芬,朱宁昌,等编.液体火箭发动机原理.北京:宇航出版社,1993
    • Relative Articles
    • Supplements(0)
    • Cited By
  • 加载中

Catalog

    通讯作者: 陈斌, bchen63@163.com
    • 1. 

      沈阳化工大学材料科学与工程学院 沈阳 110142

    1. 本站搜索
    2. 百度学术搜索
    3. 万方数据库搜索
    4. CNKI搜索
    Get Citation
    PDF
    XML

    Article Metrics

    Article views(2644) PDF downloads(1074) Cited by()
    Proportional views
    Related

    Copyright © Journal of Beijing University of Aeronautics and Astronautics

    Address: Editorial Department of Journal of Beijing University of Aeronautics and Astronautics, 37 Xueyuan Road, Haidian District, Beijing Post Code: 100191 Email: jbuaa@buaa.edu.cn

    Supported by: Beijing Renhe Information Technology Co., Ltd.    

    /

    DownLoad:  Full-Size Img  PowerPoint
    Return
    Return