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二元高超声速进气道自起动特性试验

南向军 张蒙正

南向军, 张蒙正. 二元高超声速进气道自起动特性试验[J]. 航空动力学报, 2016, 31(10): 2479-2484. doi: 10.13224/j.cnki.jasp.2016.10.022
引用本文: 南向军, 张蒙正. 二元高超声速进气道自起动特性试验[J]. 航空动力学报, 2016, 31(10): 2479-2484. doi: 10.13224/j.cnki.jasp.2016.10.022
NAN Xiang-jun, ZHANG Meng-zheng. Self-start characteristics test of 2-D hypersonic inlet[J]. Journal of Aerospace Power, 2016, 31(10): 2479-2484. doi: 10.13224/j.cnki.jasp.2016.10.022
Citation: NAN Xiang-jun, ZHANG Meng-zheng. Self-start characteristics test of 2-D hypersonic inlet[J]. Journal of Aerospace Power, 2016, 31(10): 2479-2484. doi: 10.13224/j.cnki.jasp.2016.10.022

二元高超声速进气道自起动特性试验

doi: 10.13224/j.cnki.jasp.2016.10.022
详细信息
    作者简介:

    南向军(1985-),男,陕西西安人,高级工程师,博士,主要从事内流气体力学研究.

  • 中图分类号: V23

Self-start characteristics test of 2-D hypersonic inlet

  • 摘要: 为了研究二元高超声速进气道的自起动特性,针对一带前掠侧板的混压式二元进气道,在来流马赫数为4和3.5状态开展了风洞试验,利用反压系统实现了进气道的起动、不起动和自起动过程.分析试验结果可知,进气道在来流马赫数为4和3.5状态均可自起动,但在来流马赫数为3.5,2°攻角状态不能自起动.当反压过大引起进气道不起动时,侧板根部均存在分离包、分离激波并引起溢流.从不起动状态进气道的流场结构看,该二元进气道的不起动属于软不起动,其机理不同于经典的自起动理论.但是试验结果表明,进气道的自起动马赫数仅略低于自起动理论值.当内压段入口马赫数低于2.5时,采用经典自起动理论估算自起动性能仍具有较高的精度.

     

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出版历程
  • 收稿日期:  2015-01-31
  • 刊出日期:  2016-10-28

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