埋入式进气道设计

推进技术 ›› 1998, Vol. 19 ›› Issue (4): 36-40.

埋入式进气道设计

彭成一,马强,马家驹

南京航空航天大学动力工程系;南京航空航天大学动力工程系;南京航空航天大学动力工程系

发布日期:2021-08-15

DESIGN OF THE SUBMERGED INLET

Dept of Power Engineering,Nanjing Univ.of Aeroniautics and Astronautics,Nanjing,210016;Dept of Power Engineering,Nanjing Univ.of Aeroniautics and Astronautics,Nanjing,210016;Dept of Power Engineering,Nanjing Univ.of Aeroniautics and Astronautics,Nanjing,210016

Published:2021-08-15

摘要/Abstract

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。

关键词: 埋入式进气道;进气道试验;进气道总压恢复系数

Abstract: 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

Key words: Submerged inlet +;Inlet test;Total pressure recovery coefficient of inlet

彭成一,马强,马家驹. 埋入式进气道设计[J]. 推进技术, 1998, 19(4): 36-40.