摘要
为研究不同来流马赫数、进气道出口反压、攻角以及壁面温度等参数对进气道内流特征及性能的影响,利用Fluent软件对超燃冲压发动机进气道内流场进行数值模拟。结果表明,来流马赫数小于设计马赫数时,产生溢流,且马赫数越小,溢流越大;随着反压的增大,进气道隔离段下游有明显激波串形成且不断向上游推进,导致总压恢复系数减小;攻角对进气道性能的影响与来流马赫数的影响具有一定的相似性;壁面冷却对进气道附面层发展及入口处分离包的形成有着重要的影响。
A numerical simulation was made to study effect of Mach number, back pressure, angle of attack, wall temperature on inner flow characteristics and performance of scramjet inlet. The results show that if flow Mach number is less than the designed Mach number, overflow will occur, and it becomes greater with the Mach number decrease. With increment of back pressure, the downstream isolation part has obvious shock train which goes upstream, causing decrease of the total pressure recovery coefficient, the influence of attack angle on inlet performance has certain similarities with that of flow Mach number. Wall cooling has an important influence on boundary layer de- velopment and formation of separation at the inlet.
出处
《弹箭与制导学报》
CSCD
北大核心
2015年第3期93-98,共6页
Journal of Projectiles,Rockets,Missiles and Guidance
