摘要
根据火箭发动机的推力公式及空气动力学有关理论,导出在小斜切角喷管内气体流动的特性、推力的变化规律,并给出喷管的设计方法.
In this paper, the aerodynamic performance and the thrust performance of the small bevel nozzle of rocket engines are developed based on thrust equation of rocket engines and theories in aerodynamics. A design method of this kind of nozzles is also presented.
出处
《推进技术》
EI
CAS
CSCD
北大核心
1989年第1期14-18,42,共6页
Journal of Propulsion Technology
关键词
斜置喷管
推力
火箭发动机
喷管
导弹
Canted nozzle,Thrust,Approximate,calculation,Roeket enginenozzle
