Volume 22 Issue 12
Dec.  2007
Turn off MathJax
Article Contents
Article Navigation >  Journal of Aerospace Power  > 2007  >  22(12): 2012-2017
JIE Ke, YANG Zhan-yu, ZHAO Lü-shun, LIU Jian, WANG Hong-ming, HUANG Yong, SHAN Peng. Cold flowfield experiment study of an inlet Mach number 2.5 scramjet combustor with a stream-wise vortices mixer between supersonic/subsonic-pilot-combustion flow[J]. Journal of Aerospace Power, 2007, 22(12): 2012-2017.
Citation: JIE Ke, YANG Zhan-yu, ZHAO Lü-shun, LIU Jian, WANG Hong-ming, HUANG Yong, SHAN Peng. Cold flowfield experiment study of an inlet Mach number 2.5 scramjet combustor with a stream-wise vortices mixer between supersonic/subsonic-pilot-combustion flow[J]. Journal of Aerospace Power, 2007, 22(12): 2012-2017.
shu

Cold flowfield experiment study of an inlet Mach number 2.5 scramjet combustor with a stream-wise vortices mixer between supersonic/subsonic-pilot-combustion flow

  • School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

  • Received Date: 2006-11-07
  • Rev Recd Date: 2007-03-20
  • Publish Date: 2007-12-28
    Abstract
  • An experimental study of cold flow field was conducted under entrance Mach number 2.5 on a supersonic combustor experiment rig with subsonic pilot combustor and stream-wise vortices mixer.The experiment result suggests that the up-wall static pressure distribution of wall surface and shock wave structure coincide with the CFDcalculation results,and the full flow field supersonic combustor reaches the design state.The cold test data and CFDcalculation data under 2.5Mach provide a basis for ignition test.

     

    • FullText(HTML)
  • loading
    • References(7)
  • [1]
    Ferri A,Mixing-controlled supersonic combustion[J].Ann.Rev.Fluid Mech.,1973,5:301-338.
    [2]
    Gutmark E J,Schadow K C,Yu K H.Mixing enhancement in supersonic free shear flow[J].Ann.Rev.Fluid Mech.,1995,27:375-417.
    [3]
    Campuzano M F,Dang T Q.Numerical study of lobed-mixer fuel-injection strut in scramjet engine[R].AIAA 95-2449.
    [4]
    Sunami T,Wendt M N,Nishioka M.Supersonic mixing and combustion control using streamwise vortices[R].AIAA 98-3271.
    [5]
    Situ M,Wang C,Lu H P,et al.Basic design of two combustion ramjet[R].AIAA 2002-3764.
    [6]
    赵吕顺,单鹏,刘建,等.碳氢燃料流向涡掺混超燃模型燃烧室冷态流场数值研究[J].空气动力学学报,2006,24(3):340-345.ZHAO Lushun,SHAN Peng,LIU Jian,et al.Numerical study of the cold flowfield of a hydrocarbon fueled model scramjet combustor with a streamwize vortices mixer[J].Acta Aerodynamica Sinica,2006,24(3):340-345.
    [7]
    赵吕顺.碳氢燃料流向涡掺混超燃冲压模型发动机冷态流场数值研究[D].北京:北京航空航天大学,2006.ZHAO Lüshun.Numerical study of the cold flowfield of a hydrocarbon fueled model scramjet engine with a streamwise vortices mixer[D].Beijing:Beijing University of Aeronautics and Astronautics,2006.
    • 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(1291.0KB)
    XML

    Article Metrics

    Article views (1673) PDF downloads(535) Cited by()
    Proportional views
    Related

    Copyright © 《Journal of Aerospace Power》 All Rights Reserved.

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

    /

    DownLoad:  Full-Size Img  PowerPoint
    Return
    Return