摘要
激波/附面层干扰现象的存在严重影响超声进气道的气动性能和稳定工作范围。经过50多年的研究和实践,引气作为主动控制的有效方式,现已广泛用于超声进气道的流动控制。从附面层控制引气和稳定性控制引气两个方面对引气在超声进气道中的研究应用进行了回顾。阐述并总结了引气对激波/附面层干扰的控制机理及其对超声进气道流动稳定性的影响,展望了高超声速进气道中引气技术的发展趋势。
Shock/boundary layer interaction severely impairs the aerodynamic performance and stability margin of the supersonic inlet.In the past 50 years,as one of the efficiency ways of active control,bleeding has been widely used to control the supersonic inlet flow for better performance and stability.Researches on supersonic inlet bleeding are reviewed from the perspective of how bleeding is used in boundary layer control and stable flow control.The control mechanism on the shock/boundary layer interaction and the influence on the stability of supersonic inlet flow are discussed,with a prospect on the application trend of supersonic inlet bleeding.
出处
《航空工程进展》
2013年第1期1-9,16,共10页
Advances in Aeronautical Science and Engineering
基金
航空科学基金(2012ZBN3)
关键词
超声进气道
引气
激波
附面层干扰
附面层控制
supersonic inlet
bleeding
shock/boundary layer interaction
boundary layer control
