侧压式超燃进气道流场特性研究  

INVESTIGATION ON SIDEWALL COMPRESSION SCRAMJET INLET

作　　者：向安宇[1] 岳连捷[1] 肖雅彬[1] 王世芬[1] 陈立红[1] 张新宇[1] 

机构地区：[1]中国科学院力学研究所高温气体动力学重点实验室,北京100080

出　　处：《力学与实践》2007年第3期7-10,共4页Mechanics in Engineering

摘　　要：应用表面油流和压力测量技术,结合数值模拟方法研究了超燃冲压发动机侧压式进气道无支板和有支板两种典型工况的基本流动特性．结果表明:由侧壁诱发的后掠激波与底板边界层相互作用,形成一对逆向旋转的漩涡,该漩涡在下游不断发展并偏离底板,在出口截面形成一个低马赫数低总压区;支板的引入增加了压缩率,但同时导致底板与侧壁边界层严重分离,使进气道性能偏离设计工况．The flow field in a sidewall compression scramjet inlet is studied using the surface oil dot visualization, pressure measurements and numerical simulations. Two types of sidewall scramjet inlets with or without a strut are investigated. It is shown that a pair of converse vortices emanate from the fin-plate junction and then depart from the baseplate, which results in a region with low Mach number and low total pressure at the inlet exit. Furthermore, it is shown that the boundary layer separation on the sidewall and baseplate resulting from a strut degrades the performance of the inlet.

关 键 词：超燃冲压发动机 侧压式进气道 流场显示 

分 类 号：V235.21[航空宇航科学与技术—航空宇航推进理论与工程]