导弹尾喷流对机翼的气动影响  

Airfoil Pneumatic Impact of Missile Exhaust Jet Stream

作　　者：秦可伟[1] 马贵春[1] 姚光生[1] 席园[1] 

机构地区：[1]中北大学机电工程学院,太原030051

出　　处：《弹箭与制导学报》2014年第1期123-125,195,共4页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：文中研究分析了无人机发射导弹时,导弹尾喷流对载机机翼的气动性能产生的影响;文中采用动态非结构网格技术,湍流模型为k-ω二方程模型,分析模拟了导弹发射初始阶段过程中不同距离对机翼气动性能的影响变化;分析结果表明,导弹发射初始阶段的尾喷流极大的改变了机翼周围的流场结构,对机翼的气动性能产生显著的影响;其研究结果对无人机的安全飞行具有一定的参考价值。In this article, the effect of missile＇ s exhaust jet on airfoil aerodynamic performance of UAV when missile launching was ana- lyzed. The dynamic unstructured grids and turbulence model of k-omega two-equation model were adopted for simulating airfoil aerodynamic performance change affected by different distance in the process of initial launching stage. The result shows that the exhaust jet stream in the initial phase of the missile launching greatly changes the flow field structure around the airfoil and also has significant impact on the aer- odynamic performance of the airfoil. This research finding has a certain reference value on the safety of UAV flight.

关 键 词：无人机 导弹尾喷流 动态非结构网格 数值模拟 FLUENT 

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]