摘要
本文介绍了亚燃、超燃双重燃烧进气分流的物理数学模型以及应用Euler方程组求解分流流场的数值计算方法,最后给出了计算的初步结果.
This paper describes the physico-mathematical model for entrance flow in a dual combustion ramjet.
Combustor and the numerical calculation method for solving the flow field by using Eular equations, also discusses the preliminary result of computation.
出处
《推进技术》
EI
CAS
CSCD
北大核心
1991年第3期54-61,47,共9页
Journal of Propulsion Technology
关键词
亚音速燃烧
超音速燃烧
数值解
航空发动机
Subsonic combustion, Supersonic combustion,Air flow, Assignment, Numerical solution
