流线追踪Busemann进气道设计参数的选择  

Selection of design parameters for streamtraced hypersonic Busemann inlets

作　　者：孙波[1] 张堃元[1] 金志光[1] 王成鹏[1] 

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016

出　　处：《推进技术》2007年第1期55-59,共5页Journal of Propulsion Technology

基　　金：国家"八六三"基金项目(2003AA723020)

摘　　要：为了研究型面设计马赫数、唇口偏移量对流线追踪Busemann进气道设计点性能的影响规律,寻求最佳性能的进气道,对设计马赫数为6,具有不同型面设计马赫数和唇口偏移量的流线追踪进气道进行了数值模拟。研究表明:选取低于马赫数6的型面设计马赫数,可获得较高的流量系数和增压比,而其压缩效率并不低;进气道唇口偏移量增大,会导致流量系数、增压比变小,但却有利于减小进气道内的分离程度,还会影响隔离段内的流动,因此唇口偏移量的选取需要综合考虑。Numerical simulation of a series of streamtraced hypersonic Busemann inlets have been conducted at Mach 6 to study the influence of conical flowfield design Mach number Mα1 and cowl offset d/R1 on inlet performance. The results show that small conical flowfield design Mach number Mα1 should be used in order to obtain higher mass capture ratio and pressure ratio while the compression efficiency is not low. However the exit flowfield distortion tend to be more violent. Higher cowl offset d/R1 leads to lower mass capture ratio and pressure ratio and it can ease boundary layer separation in the inlet.

关 键 词：超燃冲压发动机 Busemann进气道^+ 流线追踪 设计参数 

分 类 号：V235.213[航空宇航科学与技术—航空宇航推进理论与工程]