北京航空航天大学学报 ›› 2011, Vol. 37 ›› Issue (2): 227-230,236.

• 论文 • 上一篇    下一篇

不同飞行条件下反流控制矢量喷管的内流特性

邹欣华, 王强   

  1. 北京航空航天大学 能源与动力工程学院, 北京 100191
  • 收稿日期:2009-12-17 出版日期:2011-02-28 发布日期:2011-03-05
  • 作者简介:邹欣华(1982-),女,山东青岛人,博士生,xinhua725@sina.com.

Internal performance of counterflow thrust vectoring nozzle under different flight conditions

Zou Xinhua, Wang Qiang   

  1. School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100191, China
  • Received:2009-12-17 Online:2011-02-28 Published:2011-03-05

摘要: 利用数值模拟方法,分析了不同飞行条件下反流控制矢量喷管的内流特性.结果表明:在所研究的范围内,静态条件下,不发生主流附着的情况下,所研究的2种缝宽喷管模型产生反向二次流的抽吸压强范围分别为60 795~87 139.5 Pa,50 662.5~91 192.5 Pa;且矢量角随着抽吸压强的增大而减小,推力系数则随之增大.在外流马赫数为0.6和1.2时,对于较小缝宽的喷管模型,均有不同程度的主流附着现象发生,无法应用于实际的矢量流场控制.对于较大缝宽喷管模型,在马赫数为0.6时,不发生主流附着的情况下,产生反流的抽吸压强为40 530~87 139.5 Pa.而马赫数为1.2时在所研究的二次压强下都无反流产生.

Abstract: An analysis of the impact of internal performance on the counterflow thrust vectoring nozzle under different flight conditions was presented by numerical simulation. The results show in static conditions counterflow phenomena occurs on two nozzles of different slot hights when the secondary pressure is at 60 795-87 139.5 Pa and 50 662.5-91 192.5 Pa without jet attachment. And with the secondary pressure increasing ,the pitch-thrust-vector angles decrease and thrust ratios increase. When the Ma number is 0.6 and 1.2, jet attachment occurs on the nozzle with smaller slot hight and can not apply to actual fluidic control. But to the nozzle with larger slot hight, when the Ma number is 0.6,counterflow phenomena occurs at secondary pressure 40 530-87 139.5 Pa without jet attachment. When the Ma number is 1.2,there is no counterflow phenomena at considered secondary pressure.

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