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增强型双喉道射流推力矢量喷管的流动特性试验

周辉华 谭慧俊 周慧晨 蔡建刚

周辉华, 谭慧俊, 周慧晨, 蔡建刚. 增强型双喉道射流推力矢量喷管的流动特性试验[J]. 航空动力学报, 2013, 28(7): 1576-1581.
引用本文: 周辉华, 谭慧俊, 周慧晨, 蔡建刚. 增强型双喉道射流推力矢量喷管的流动特性试验[J]. 航空动力学报, 2013, 28(7): 1576-1581.
ZHOU Hui-hua, TAN Hui-jun, ZHOU Hui-chen, CAI Jian-gang. Flow characteristic experiment on vector-enhanced dual-throat thrust-vectoring nozzle[J]. Journal of Aerospace Power, 2013, 28(7): 1576-1581.
Citation: ZHOU Hui-hua, TAN Hui-jun, ZHOU Hui-chen, CAI Jian-gang. Flow characteristic experiment on vector-enhanced dual-throat thrust-vectoring nozzle[J]. Journal of Aerospace Power, 2013, 28(7): 1576-1581.

增强型双喉道射流推力矢量喷管的流动特性试验

Flow characteristic experiment on vector-enhanced dual-throat thrust-vectoring nozzle

  • 摘要: 对一种增强型双喉道射流推力矢量喷管开展了内部流动特性的试验研究,获得了其在不同次流压比状态下的内流结构和沿程静压分布.试验结果显示:在基准双喉道矢量喷管尾部附加扩张段后,能够以2.8%的次流消耗率获得超过20°的平均气流偏角,这表明通过附加扩张段来增加喷管矢量角的设计概念是可行的.在凹腔内,增强型双喉道射流推力矢量喷管的静压分布规律与基准双喉道矢量喷管一致,但在附加的扩张段内,下壁面的压强要明显高于上壁面,这正是其推力矢量角得到显著增大的原因.随着次流压比的增加,喷管获得的推力矢量角单调增加,但是喷管附加扩张段的矢量增强效果基本维持不变.

     

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出版历程
  • 收稿日期:  2012-10-11
  • 刊出日期:  2013-07-28

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