高超声速进气道附面层分离无源被动控制

推进技术 ›› 2011, Vol. 32 ›› Issue (4): 455-460.

高超声速进气道附面层分离无源被动控制

苏纬仪,张堃元,金志光

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;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
作者简介:苏纬仪(1979—),男,博士生,研究领域为高超声速推进技术。E-mail:suweiyi@sina.com
基金资助:
国家自然科学基金(90916029);中国博士后科学基金(20100481139)。

Adaptive passive control on hypersonic inlet boundary layer separation

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

Published:2021-08-15

摘要/Abstract

摘要： 为了控制超燃冲压发动机进气道唇口反射激波诱导的附面层分离,根据其流动特征,提出了附面层泄除-吹除互相驱动的自适应、无源、被动控制方案。并采用空间HLLE格式、LU-SGS隐式推进、多块结构网格的有限体积法数值模拟程序对该流动现象进行了数值模拟。数值结果表明,施加自适应无源被动控制后,分离区长度减小为无控制时的45%,控制区域的总压恢复系数和流场均匀性提高。从而证实了自适应、无源、被动控制抑制高超声速进气道附面层分离的可行性。

关键词: 高超声速进气道; 被动控制; 激波/边界层相互作用⁺

Abstract: In order to control the separation induced by cowl reflected shock waves in scramjet inlet, based on its flow characteristic, an adaptive passive control method in which bleeding and blowing is self-driven by each other was proposed. The flow was simulated numerically with HLLE schemes,LU-SGS multiblock structure finite volume methods code. The numerical results show that with the adaptive passive control, the separation bubble length was reduced to 45% of its original length,and the low total pressure recovery coefficient was improved. Thus the possibility of the adaptive passive control methods were demonstrated.

Key words: Hypersonic inlet; Passive control method; Shock-wave/boundary layer interactions⁺

苏纬仪,张堃元,金志光. 高超声速进气道附面层分离无源被动控制[J]. 推进技术, 2011, 32(4): 455-460.