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混合模块发动机超燃模块进气道的数值仿真
引用本文:李璞,郭荣伟.混合模块发动机超燃模块进气道的数值仿真[J].南京航空航天大学学报,2009,41(2).
作者姓名:李璞  郭荣伟
作者单位:南京航空航天大学能源与动力学院,南京,210016
基金项目:国家高技术研究发展计划(863计划) 
摘    要:对适用于轴对称混合模块发动机的超燃模块进气道进行了初步设计研究.采用数值方法,重点研究了中心锥压缩角、肩部倒圆半径、唇罩侧板前缘角度、隔离段长度、隔离段偏距等几何设计参数对进气道性能的影响规律,并提出了参数选择建议.结果表明:在研究范围内,中心锥压缩角、肩部倒圆半径、唇罩侧板前缘角度以及隔离段长度等参数对进气道性能影响较大,而隔离段偏距的影响较小.

关 键 词:航空、航天推进系统  高超声速流  进气道  混合模块发动机  超燃模块  数值分析

Numerical Simulation of Hypersonic Inlets for Scramjet Modules of Dual Combustor Ramjet
Li Pu,Guo Rongwei.Numerical Simulation of Hypersonic Inlets for Scramjet Modules of Dual Combustor Ramjet[J].Journal of Nanjing University of Aeronautics & Astronautics,2009,41(2).
Authors:Li Pu  Guo Rongwei
Institution:College of Energy and Power Engineering;Nanjing University of Aeronautics & Astronautics;Nanjing;210016;China
Abstract:Hypersonic inlets for scramjet modules of dual combustor ramjet are studied.The influence of the geometry parameters is mainly studied on the inlet performance by using numerical method.The geometry parameters include the cone angle,the radius of the shoulder,the leading edge angle of the side wall of the cowl,the length of the isolator,and the offset of the isolator.Results indicate that the geometry parameters,such as the cone angle,the radius of the shoulder,the leading edge angle of the side wall of the...
Keywords:aerospace propulsion system  hypersonic flow  inlet  dual combustor ramjet  scramjet module  numerical analysis  
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