| 喷流反压模拟技术及在高超声速进气道实验中的应用 |
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| 引用本文： | 孙姝,张红英,程克明,伍贻兆.喷流反压模拟技术及在高超声速进气道实验中的应用[J].航空动力学报,2007,22(10):1667-1672. |
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| 作者姓名： | 孙姝 张红英 程克明 伍贻兆 |
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| 作者单位： | 南京航空航天大学,高超气动研究中心(HARC),南京,210016 |
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| 基金项目： | 中国博士后科学基金
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江苏省博士后科学基金
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国防科工委基础科研项目 |
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| 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.
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| 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 喷流技术 反压 模拟技术 高超声速进气道 进气道实验 应用 experiment inlet hypersonic application injection cavity simulation pressure 流态 再起动 时间 风洞实验 总压 环境 |
| 文章编号： | 1000-8055(2007)10-1667-06 |
| 收稿时间： | 2007/5/17 0:00:00 |
| 修稿时间： | 2007年5月17日 |
Back pressure simulation by cavity injection and its application in hypersonic inlet experiment |
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| SUN Shu,ZHANG Hong-ying,CHENG Ke-ming and WU Yi-zhao.Back pressure simulation by cavity injection and its application in hypersonic inlet experiment[J].Journal of Aerospace Power,2007,22(10):1667-1672. |
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| Authors: | SUN Shu ZHANG Hong-ying CHENG Ke-ming and WU Yi-zhao |
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| Institution: | Hypersonic Aerodynamics Research Center, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;Hypersonic Aerodynamics Research Center, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;Hypersonic Aerodynamics Research Center, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;Hypersonic Aerodynamics Research Center, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China |
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| Abstract: | 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. |
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| Keywords: | aerospace propulsion system back pressure simulation by cavity injection hypersonic inlet wind tunnel test |
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