论文部分内容阅读
为了获得头部偏角对气动特性的影响规律,首先对弹体表面不同位置的压力变化进行了试验,并以此修正和验证基于头部偏转弹的数值计算模型,并进一步计算不同马赫数和不同头部偏角情况下对升力、阻力和俯仰力矩影响规律。结果表明,头部偏转对弹体表面影响效果十分显著,远远大于同一角度攻角对压力大小的改变量。较小头部偏角和马赫数下的阻力与原型弹偏差不大;随着头部偏角的增加,升力和俯仰力矩会迅速增加。对于在某个头部偏角情况下,存在唯一一个使飞行稳定的最大马赫数。
In order to obtain the influence law of the head deflection on the aerodynamic characteristics, the pressure changes at different positions on the surface of the projectile were tested first, and then the numerical calculation model based on the head deflection projectile was modified and verified. Furthermore, Effects of different head declination on lift, drag and pitching moment. The results show that the effect of head deflection on the surface of the projectile is very significant, which is much larger than the change of pressure on the angle of attack at the same angle. The resistance of the smaller head and the Mach number is not significantly different from that of the prototype bomb; as the head declination increases, the lift and pitch moments increase rapidly. For a declination of a head, there is only one maximum Mach number that stabilizes the flight.