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超声速弹箭表面的流体分离是影响飞行稳定的主要影响因素之一。研究表明,微楔涡流发生器可有效控制超声速流体边界层的流动分离。该文基于制式122火箭弹,通过在弹肩前端安装微楔来研究边界层流动分离控制对火箭弹气动性能的影响。运用DES方法数值模拟了122火箭弹在有无加装微楔条件下的流场变化,对比分析了微楔对弹体表面边界层结构以及弹气动数据的改变,讨论了微楔对弹的气动力及稳定性作用。数值结果表明,微楔可以抑制弹体表面流体分离,提高火箭弹的升力及俯仰力矩,减小马格努斯力矩,有利于提高其飞行稳定性及射击精度,可为相关旋转火箭弹的改进提供指导。
Fluid separation of the surface of an ultrasonic projectile is one of the main factors affecting the stability of the flight. The research shows that micro wedge vortex generator can effectively control the flow separation of supersonic fluid boundary layer. In this paper, based on the 122 rocket, the effect of the boundary layer flow separation control on the aerodynamic performance of the rocket was studied by installing micro wedges on the front of the shoulder. The flow field of 122 rocket with or without micro wedge was numerically simulated by DES method. The micro wedge was used to analyze the change of the boundary layer structure and the aerodynamic data of the projectile. The effects of micro wedges on the gas Power and stability effects. The numerical results show that micro wedges can suppress the fluid separation on the surface of projectile, increase the lift and pitching moments, reduce the Magnus moment, improve the flight stability and shooting accuracy, and can improve the related rotating rockets Provide guidance.