超声速飞行器后缘舵缝隙影响研究  

Research on the Effect of Gaps on Hypersonic Aircraft Steering Rudder

作　　者：王明昆[1] 马林静[1] 张元静[1] 周丹杰[1] 

机构地区：[1]北京机电工程研究所,北京100074

出　　处：《战术导弹技术》2017年第2期34-40,共7页Tactical Missile Technology

摘　　要：针对某超声速飞行器,采用数值模拟方法研究了不同弦向缝隙下机翼与后缘舵之间的绕流特性,在兼顾亚声速气动特性的基础上获得了缝隙对舵效及气动性能的影响规律。结果表明,亚声速时舵效随缝隙的增大降低较多;超声速时缝隙对舵效的影响较亚声速小,当缝隙为10 mm时飞行器的舵效及气动性能最优,研究结果可为超声速飞行器后缘舵设计提供定性的参考依据。Aimed the certain hypersonic aircraft, the flow around features between the wing and the steer- ing rudder under the different gaps are focued on by numerical simulates. Then the influence law of the gap to the rudder surface efficiency and the aerodynamic performance on the basement of considering sub- sonic flow is obtained. The results show that the rudder surface efficiency declines much as the gaps in- creases in subsonic, and the influence on rudder surface efficiency in supersonic is smaller than subson- ic, the rudder surface efficiency and the aerodynamic characteristics reaches the best when the gap size is lOmm. The research result can provide the qualitative reference to supersonic aircraft steering rudder de- sign.

关 键 词：舵面缝隙 高超声速 舵效 后缘舵设计 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]