战斗机边条翼大迎角涡升力研究  

Research on the Strake Wing Vortex Lift of Flighter at High Angle of Attack

作　　者：段卓毅[1] 陈迎春[2] 赵克良[2] 司江涛[2] 

机构地区：[1]西北工业大学飞机系,陕西西安710072 [2]西安飞机设计研究所二室,陕西西安710089

出　　处：《飞行力学》2003年第3期18-20,共3页Flight Dynamics

摘　　要：利用求解(翼身组合体)欧拉方程的数值计算方法,对边条翼布局飞机的气动力特性进行了研究,计算并分析了边条翼对机翼表面压力分布的影响规律以及对全机升力特性尤其是大迎角升力特性的影响。最后,给出了带边条翼战斗机大迎角涡升力特性的研究结论。Some results of the strake wing vortex lift of a flighter at high angle of attack are presented in this paper. The lift curve and the curve of pressure distribution are gotten by solving the Euler equation for a wingbody configuration. The influence caused by the strake on the curve of pressure distribution of wing is presented. The reason why the strake has an advantage in the lift characteristic of a battle aircraft at high angle of attack is discussed in detail. 

关 键 词：战斗机 边条翼 大迎角 涡升力 有限体积法 计算 

分 类 号：V212.1[航空宇航科学与技术—航空宇航推进理论与工程]