文中对双下侧进气道布局的导弹进行了数值建模,并利用专业流体计算软件对导弹的超音速特性进行了数值模拟,发现在零攻角时全弹法向力为负值,这对长时间巡航的导弹是不利的因素。针对这种现象,文中对各个气动组件进行详细分析,研究其流场特性和负法向力产生的机理,找出全弹法向力为负的原因来源于各气动组件的相互影响,并在结尾给出了适当的优化建议。

The missile with two lower inlets was numerically simulated in this paper. It is found that the normal force of missile is negative at zero attack angles; this is bad for long range missile. Focused on this performance, the effect of every aerodynamic part was analyzed, the flow filed characteristics and generation mechanism of negative normal force at zero angle-of-attack were studied, it was found that the reason why the missile's normal force is negative originates from the interaction of aerodynamic components, the improvement advice was given.