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超燃冲压发动机进气道不起动仿真研究
引用本文:鲍文,常军涛,郭新刚,崔涛.超燃冲压发动机进气道不起动仿真研究[J].航空动力学报,2005,20(5):731-735.
作者姓名:鲍文  常军涛  郭新刚  崔涛
作者单位:哈尔滨工业大学,能源科学与工程学院,黑龙江,哈尔滨,150001
基金项目:863国家高技术术研究发展计划资助
摘    要:对超燃冲压发动机进气道-隔离段进行了二维稳态流场数值模拟,给出了超燃冲压发动机进气道起动到不起动整个过程的数值模拟结果。得到了不同压比下、不同攻角下进气道-隔离段内部流场等压线图,分析了进气道-隔离段壁面静压分布特性,初步给出了进气道不起动状态的判断准则。

关 键 词:航空、航天推进系统  超燃冲压发动机  进气道  不起动  判断准则
文章编号:1000-8055(2005)05-0731-05
收稿时间:2004/7/22 0:00:00
修稿时间:2004年7月22日

Unstart Simulation of Scramjet Inlets
BAO Wen,CHANG Jun-tao,GUO Xin-gang and CUI Tao.Unstart Simulation of Scramjet Inlets[J].Journal of Aerospace Power,2005,20(5):731-735.
Authors:BAO Wen  CHANG Jun-tao  GUO Xin-gang and CUI Tao
Institution:School of Energy Science and Engineering,Harbin Institute of Technology,Harbin150001,China;School of Energy Science and Engineering,Harbin Institute of Technology,Harbin150001,China;School of Energy Science and Engineering,Harbin Institute of Technology,Harbin150001,China;School of Energy Science and Engineering,Harbin Institute of Technology,Harbin150001,China
Abstract:The 2-D internal steady flow of the scramjet inlet-isolator was numerically simulated by the prevailing software,the numerical simulation results of the process from start to unstart in the scramjet inlet were presented.The static pressure contours of the scramjet inlet-isolator under different back pressure and angle of attack were given.The distribution of static pressure of inlet-isolator was analyzed and the unstart judgement criterion was given.
Keywords:aerospace propulsion system  scramjet  inlet  unstart  judgement criterion
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