一种径向布局双模块高超音速进气道起动特性研究  

Study on Start Characteristic of Hypersonic Radial Dual-modules Inlet

作　　者：马高建[1] 贺永杰[1] 

机构地区：[1]中国空空导弹研究院,洛阳471009

出　　处：《科学技术与工程》2013年第21期6347-6353,共7页Science Technology and Engineering

摘　　要：对一种定几何径向布局轴对称亚燃/超燃高超音速进气道的起动过程、亚燃室反压引起的不起动、飞行速度引起的不起动和再起动过程的非定常流态进行了数值仿真。仿真结果表明:亚燃进气道起动过程中,由于亚燃进气道采用附面层抽吸措施,起动和再起动能力较好;而超燃进气道起动过程中,容易受到亚燃进气道压缩波系的影响。An unsteady numerical simulation was carried out on the start,unstart and restart performances of a fixed-geometry,radial-arrangement,axisymmetric hypersonic inlet for ramjet module and scramjet module due to changing free stream Mach number and pressure of ramjet combustion.The results show that,the start and restart performances of hypersonic inlet for ramjet module,which is very well because of using boundary layer suction.The shocks-arrangement of hypersonic inlet for scramjet module is easily influenced by hypersonic inlet for ramjet module in the start process.

关 键 词：双模块高超音速进气道 轴对称 径向布局 起动 再起动 附面层抽吸 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程]