二维非常规压缩型面超/高超声速进气道的设计概念

推进技术 ›› 2004, Vol. 25 ›› Issue (3): 226-229.

二维非常规压缩型面超/高超声速进气道的设计概念

金志光,张堃元

南京航空航天大学能源与动力学院江苏南京210016;南京航空航天大学能源与动力学院江苏南京210016

发布日期:2021-08-15

Concept of a two-dimensional supersonic/hypersonic inlet with a non-conventional compression wall

Coll. of Energy and Power, Nanjing Univ. of Aeronautics and Astronautics, Nanjing 210016, China;Coll. of Energy and Power, Nanjing Univ. of Aeronautics and Astronautics, Nanjing 210016, China

Published:2021-08-15

摘要/Abstract

摘要： 为了提高满足一定尺寸要求的进气道的性能,提出了一种非常规压缩型面进气道,并用数值模拟手段对该进气道和常规的二维斜楔式进气道的性能进行了比较。数值模拟结果表明,设计工况下该进气道能够获得跟常规二维斜楔式进气道大致相当的气动性能。非设计工况下,该进气道性能优于常规进气道。一体化设计时,该进气道对保持前机体来流附面层的稳定性十分有利。

关键词: 超声速进气道;高超声速进气道;二维流;非常规压缩型面+;激波;一体化设计

Abstract: An inlet with non-conventional compression wall is designed in order to improve the performance of inlets constrained by its size. Comparisons by means of numerical simulation are made between this inlet and the normal two-dimensional ramp inlet. It is shown that at the design point the inlet with the non-conventional compression wall has the similar performance as the normal one, but has a better performance at off-design point. This demonstrates that for propulsion-airframe integration, this genus of inlet would be advantageous in keeping the stability of boundary layer coming from the forebody.

Key words: Supersonic inlet;Hypersonic inlet;Two dimensional flow;Non-conventional compression wall~+;Shock wave;Integrated design

金志光,张堃元. 二维非常规压缩型面超/高超声速进气道的设计概念[J]. 推进技术, 2004, 25(3): 226-229.