吸气式导弹气动力预计方法研究

有攻角条件下在二元进气道壳体的尖锐棱角上会产生脱体涡,使壳体升力增长,导致进气道壳体的升力大于将壳体压扁后形成的小展弦比薄翼的升力。二元进气道阻力对全弹阻力有很大贡献,通气状态下则存在复杂的内外流干扰导致难于计算。本文基于风洞实验数据库和CFD数值计算解,发展了一种可计算带二元进气道吸气式导弹气动力的计算方法,获得了与实验数据吻合很好的计算结果,该方法可用于此类导弹的选型设计。

An aerodynamic prediction method for air-breathing missile

The detached vortex can be generated from the sharp edge of the 2D inlet of air-breathing missile at some angle of attack.It makes the lift of air-breathing missile larger than that of the missile with thin wing of the same area.The drag of air-breathing missile is usually difficult to be calculated because of the complex interference between the outer flow and the inlet flow.An empirical method based on experimental database from wind tunnel and on the result of CFD is developed to predict the aerodynamic characteristics of air-breathing missile.Good agreement between the calculated results and experimental data is obtained.It indicates that this method can be applied in air-breathing missile design.