Bump进气道设计与试验研究

对一种先进的无隔道超音速进气道(Bump或者DSI)进行了设计方法和风洞试验研究。研究表明:Bump进气道性能优异,并且取消了传统的超音速战斗机进气道设计中的附面层隔道、泄放系统和旁路系统,使得飞机阻力小、重量轻、可靠性高。Bump进气道是根据锥型流理论,采用乘波原理设计的。即用机身形面去截取锥形流场,在此范围内进行压缩面的设计,由于锥型波波后产生等熵压缩,在压缩面展向形成一定的压力梯度,将附面层排出进气道口外。

The research of bump inlet design and test

An advanced Diverterless Supersonic Inlet(DSI or Bump) is introduced in this paper.The bump inlet has an excellent aerodynamic performance and eliminates many of the traditional complex features associated with boundary layer management:the diverter,bleed system and bypass system.By eliminating these features,the inlet aperture is integrated with the aircraft forebody,it could produce the best value configuration with low drag,low weight,and high reliability.The bump inlet is designed according to the waverider theory of a conical flow field which is intercepted by the aircraft forebody and used to define the bump compression surface.Because the cone flow produces isentropic compression behind the shock,the defined surface has spanwise pressure gradients which help to divert the boundary layer away from the inlet entry.