在末端大攻角飞行条件下,某战术导弹法向力系数斜率降低导致法向过载不足。为解决此问题,文中开展了边条翼在导弹气动外形设计中的应用研究。通过数值仿真和风洞试验的方法,对某大展弦比弹翼布局的战术导弹在增加边条翼前后的气动特性进行了分析。结果表明,在大攻角条件下,边条翼的引入大幅提升了导弹的法向力系数斜率,从而大幅提升了其法向过载,改善了其机动性。

At the end of a high angle of attack flight conditions,the normal force coefficient slope reduce of tactical missile lead to the lack of normal overload.In order to solve this problem,we carried out the research that at the strake wing missile aerodynamic shape design.Through the simulation calculation and wind tunnel test,the missile's aerodynamic characteristics were analyzed with or without strake wing.The results showed that,at high angle of attack conditions,the introduction of strake wing are greatly improve the missile normal force coefficient slope,thus greatly enhancing its normal overload and improve its mobility.