非对称×形折叠翼巡飞弹气动特性数值研究

为了研究非对称×形折叠翼巡飞弹的气动特性,在保证弹径、弹长、舵翼的弦长和暴露展长相同的情况下,分别开展了对称×形折叠翼气动布局与非对称×形折叠翼气动布局巡飞弹气动特性的数值模拟,对比了两者侧向力系数、滚转力矩系数、升力系数以及阻力系数,发现与×形翼气动布局相比,非对称×形折叠翼气动布局产生了侧向力与滚转力矩。进一步分析了非对称×形折叠翼气动布局产生侧向力与滚转力矩的原因。结果表明:在亚音速条件下,非对称×形折叠翼气动布局的升力系数与阻力系数随着攻角和马赫数的增大而增大; 非对称×形折叠翼气动布局由于舵翼沿着弹身是非对称布置的,导致了非对称的气动干扰,从而产生了侧向力和滚转力矩。非对称×形折叠翼气动布局的侧向力系数随着马赫数的增大而增大,随着攻角的增大呈现先增大后减小再增大的趋势,滚转力矩系数随着攻角和马赫数的变化较为复杂。

Numerical Study on Aerodynamic Characteristics ofAsymmetric X-folded Fin of Patrol Missile

In order to study the aerodynamic characteristics of patrol missile with asymmetric X-folded fin,the aerodynamic forces of the asymmetric X-folded fin aerodynamic configuration and symmetric X-folded fin aerodynamic configuration were simulated under the same conditions of diameter,length,chord length and exposed span of canard and fin. By comparing the lateral force coefficient,rolling moment coefficient,lift coefficient and drag coefficient of the asymmetric and symmetric X fin aerodynamic configurations,it was found that the asymmetric X-folded fin aerodynamic configuration yields lateral force and rolling moment. The reason of the lateral force and roll moment produced by the X-folded fin aerodynamic configuration of the folding fin were further analyzed. The results show that under subsonic conditions,the lift coefficient and drag coefficient of asymmetric X-folded fin aerodynamic configuration increase with the increase of angle of attack and Mach number. The canards and fins are arranged asymmetrically along the missile body,the asymmetric aerodynamic interference is caused,resulting in the lateral force and rolling moment. The lateral force coefficient of the asymmetric X-folded fin aerodynamic configuration increases with the increase of Mach number. With the increase of angle of attack,it first increases,then decreases and then increases. The variation of rolling moment coefficient with angle of attack and Mach number is more complex.