冲压发动机进气道不起动边界分析  

Analysis of the unstart boundary for ramjet inlets

作　　者：何保成[1] 常军涛[1] 于达仁[1] 

机构地区：[1]哈尔滨工业大学能源科学与工程学院

出　　处：《推进技术》2007年第3期269-272,共4页Journal of Propulsion Technology

摘　　要：不起动边界是超声速进气道研究的重要内容,它是进气道保护控制的基础和前提。针对这一问题,对冲压发动机进气道进行了不同边界条件下的数值模拟,对稳态流场结果进行了分析。基于仿真数据,利用量纲分析工具对进气道最大抗反压能力进行了分析,讨论并给出了两进气道流动的相似条件。分析结果表明:在不考虑攻角变化的条件下,进气道不起动边界主要与来流马赫数有关。　Unstart boundary is one of the most important issues of supersonic inlets,and also the foundation of inlet protection control.To solve this problem,the steady internal flowfield of ramjet inlets at different boundary conditions was simulated and analyzed.Based on the simulation data,the tool of dimensional analysis was introduced to find the variable describing the unstart boundary in this paper.The dimensionless pressure ratios of inlets were analyzed.The flow similar conditions of two hypersonic inlets are discussed.The results show that the unstart boundary of supersonic inlets is mainly concerned with Mach number of freestream without considering the variation of angle of attack.

关 键 词：冲压发动机^+ 进气道 不起动^+ 边界 保护控制 

分 类 号：V233.6[航空宇航科学与技术—航空宇航推进理论与工程]