关键词: 超燃冲压发动机;二元高超声速进气道;波系配置;附面层抽吸

Abstract: The paper presents the shocks arrangement of ramp compression hypersonic inlet with fixed geometry within a range of flight Mach number. The effect of internal contraction ratio was studied based on the inlet optimization design with the objective of scramjet thrust. The design methods for the inlet shocks and bleeding slots were then developed. The result reveals that an optimal inlet internal contraction ratio exists for on-design engine thrust, while the pressure ratio and mass flow capture on off-design condition increase with the internal contraction ratio. An oblique shock can be replaced by isentropic compression waves impinging into the internal duct without focus, which cancels the restriction of shock-on-lip. This modification would dramatically improve the inlet mass capture on off-design point. Moreover, the rational bleeding is proven to be viable for inlet starting, which reduced the inlet self-starting Mach number to 3.35 with a little mass loss. 

Key words: Scramjet;Ramp compression hypersonic inlet; Shocks arrangement; Boundary layer bleeding