火箭推进2011，Vol.37Issue(6)：38-42,46,6.
来流马赫数对射流矢量喷管内流场影响的动态模拟
Dynamic simulation for effect of incoming flow Mach number on internal flow field of fluidic thrust vectoring nozzle
宋亚飞 1高峰 1杨小秋2
作者信息
- 1. 空军工程大学导弹学院,陕西三原713800
- 2. 空军95100部队装备部,广东广州510405
- 折叠
摘要
Abstract
Taking the 2D convergent-divergent nozzle as a research object, the 2D unsteady Reynolds average N-S equation and RNG k-e turbulence model was utilized to study the unsteady flow field of fluidic thrust vectoring nozzle based shock control. The influence of continual variation of the incoming flow Mach number on the flow field in the nozzle is analyzed. The changing regularity of nozzle thrust performance was derived. The results show that the incoming flow Mach number causes the change of pressure round the nozzle exit, and influences the internal flow characteristics of the vectoring nozzle by the interaction of nozzle boundary layer and shock; in the subsonic free flow, with the increase of incoming flow Mach number, the thrust increases; in the transonic flow, the side thrust and axial thrust decrease hardly; when the Mach number is supersonic velocity, the thrust de-clines with the increase of Mach number; and the thrust vector angle and thrust coefficient are same as the changing regularity of side thrust and axial thrust.关键词
固体火箭发动机/射流推力矢量/二次流/内流场/数值模拟Key words
solid propellant rocket engine/fluidic thrust vector/secondary injection/internal flow field/numerical simulation分类
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宋亚飞,高峰,杨小秋..来流马赫数对射流矢量喷管内流场影响的动态模拟[J].火箭推进,2011,37(6):38-42,46,6.
