超声速混压式进气道起动与质量吸除耦合设计  

Start Design Coupled with Mass Bleed of Mixed-compression Supersonic Inlets

作　　者：孔晓俊[1] 杨铁成[1] 谷良贤[1] 龚春林[1] 

机构地区：[1]西北工业大学航天学院,西安710072

出　　处：《科学技术与工程》2011年第18期4282-4285,共4页Science Technology and Engineering

摘　　要：结合质量吸除方案,对超声速混压式进气道进行了起动耦合型面设计,并采用CFD数值模拟对进气道的总体性能进行了对比分析。研究结果表明该方案具有以下优点:1)可以提高进气道的总体性能;2)可以解决低马赫数下超声速混压式进气道的起动问题;3)可以改善高马赫数下进气道的气流分离特性。为大空域、宽马赫数工作的超声速进气道的设计提供参考。A mixed-compression supersonic axisymmetric ram jet inlet coupled with mass bleed was designed and calculational results of different flight Mach numbers are obtained after the numerical simulation.Finally the analysis of inlet performance were present in the end.According to the results of this investigation,this design has such advantages as follow： 1） The general performance of the inlet has been improved;2） It could also solve the start problem of mixed-compression supersonic inlets at low Mach number;3） the performance of flow separation at high Mach number could be improved as well.The results could provide references for the design of supersonic cruising missile＇s inlets.

关 键 词：吸气式推进系统 亚燃冲压发动机 超声速进气道 质量吸除 数值模拟 

分 类 号：V211.48[航空宇航科学与技术—航空宇航推进理论与工程]