摘要
介绍了冲压发动机进气道的设计方法,并采用FLUENT软件对单独进气道与组合体进气道流场进行了数值模拟,比较了在两种情况下进气道的气动状况,并分析了攻角对进气道流场的影响。
A way of rocket ramjet engine design was introduced . In this paper, the FLUENT software was used for numerical simulation of compounding current field caused by sole inlet and body inlet. The inlet＇s aerodynamic differences under the two conditions were compared and the attack angle＇s influence on inlet current field was analyzed.
出处
《弹箭与制导学报》
CSCD
北大核心
2008年第3期203-205,209,共4页
Journal of Projectiles,Rockets,Missiles and Guidance
关键词
超声速进气道
数值模拟
攻角
超声速导弹
supersonic inlet
numericai simulation
attack angle
supersonic missile
