摘要
为研究高超声速进气道的反压特性以及不起动/再起动特性,提出了一种凹腔喷流反压模拟技术,在实验过程中通过控制阀门的开度可方便地且迅速地调节进气道的出口反压.利用该技术,还对一种马赫数为7级的轴对称高超声速的反压特性及不起动/再起动特性进行了研究,展示了该技术的实用性.结果表明:(1)所提出的凹腔喷流技术可在进气道下游形成较为均匀的、可控的背压环境,因此可用于进气道的反压特性研究;(2)适当调节凹腔的喷流总压,并在实验中实时控制阀门的开度,凹腔喷流技术能够在较短的风洞实验时间内(约8 s)实现进气道起动、不起动、再起动流态之间的切换,因此可用于进气道的不起动/再起动特性研究.
A kind of back pressure simulation technology by cavity injection is brought forward to improve wind tunnel test capability for hypersonic inlets.During wind tunnel test process,the back pressure of inlet can be adjusted rapidly by regulating the valve of injection pipe.Utilizing this specific simulation technology, the performance at different back pressures and the unstarting/restarting characteristics of an axisymmetric inlet are investigated.The design Mach number of the inlet is 7.0.Results indicate：（1） The newly developed simulation technology can form fairly average and easily controllable back pressure downstream the inlet,so it can be used to investigate the back pressure characteristics of hypersonic inlets.（2） By regulating the valve of injection pipe,the simulation technology can realize the switch of hypersonic inlet started state and unstarted state in about 8 milliseconds,so it is suitable to investigate the starting/unstarting/restarting problem of hypersonic inlets.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2007年第10期1667-1672,共6页
Journal of Aerospace Power
基金
中国博士后基金(0601042B)
江苏省博士后基金(20060400935)
国防科工委基础预研项目(A2520060219)
关键词
航空、航天推进系统
喷流反压模拟
高超声速
进气道
风洞实验
aerospace propulsion system
back pressure simulation by cavity injection
hypersonic
inlet
wind tunnel test
