考虑附面层影响的二元混压式进气道设计  

Design of a two-dimensional mixed-compression supersonic inlet with boundary layer consideration

作　　者：骆广琦[1,2] 郑九州[2] 宋頔源[2] 

机构地区：[1]西北工业大学动力与能源学院,西安710072 [2]空军工程大学工程学院,西安710038

出　　处：《航空动力学报》2009年第9期2063-2068,共6页Journal of Aerospace Power

摘　　要：采用等激波强度的方法,考虑附面层修正,设计了一种飞行马赫数Ma=3.0的二元混压式进气道.通过数值仿真,模拟了激波-边界层的相互影响,研究了附面层抽吸对内流场的影响,获得了进气道内部复杂的流场分布,以及不同背压下进气道的起动特性.计算表明所设计的进气道性能较好,附面层抽吸对稳定正激波有明显的作用,提高了进气道抗反压能力.给出的方法可用于二元混压式进气道的初步设计和验证.Based on constant shock intensity method,a two-dimensional mixed-compression supersonic inlet was designed for flight at Mach number of 3.0.The correction was made for the effects of boundary layer.Quasi-one-dimensional analysis shows that the designed inlet has a good performance.By two-dimensional viscous simulation of inlet flows with terminal shocks,flow status of complicated flow field was presented in two-dimensional mixed-compression supersonic inlet.The reflections and intersections of various shock...

关 键 词：混压式进气道 进气道设计 数值模拟 附面层抽吸 起动特性 

分 类 号：V235[航空宇航科学与技术—航空宇航推进理论与工程]