摘要
提出了将埋入式进气道分为导流段与管道两部分的设计方案，并对此进气道进行了低速Ｍａ＝０．３７和高速Ｍａ＝０．７０的风洞试验，结果表明：新的设计方案能提高埋入式进气道的性能，使其σ≥０．９４，Δσ＜０．０１。
Submerged inlet is often considered as a slightly S curved divergent duct with no more elaboration than careful shaping of the duct entrance fo facilltate inlet flow.Performance of such an inlet is handicapped by its position inside the missle.The innovative design concept presented herein makes it possible to achieve the performance that is superior to all test results hitherto known to the author
出处
《推进技术》
EI
CAS
CSCD
北大核心
1998年第4期36-40,共5页
Journal of Propulsion Technology
关键词
飞机
埋入式
进气道
总压恢复系数
设计
Submerged inlet +,Inlet test,Total pressure recovery coefficient of inlet
