摘要
研究表明,主动式射流涡流发生器可有效控制超声速流动边界层的分离,且能根据实际情况进行自适应调节。该文基于制式122尾翼弹,通过在弹肩前端加装射流涡发生器控制边界层的流动分离,研究其对尾翼弹气动性能的影响。采用DES方法数值模拟了超声速条件下尾翼弹有无射流控制的流场变化情况,分析了加装射流前后尾翼弹表面流体边界层结构及其气动性能的变化规律。数值结果表明,射流控制可有效抑制弹体表面的流体分离,提高尾翼弹的升力与俯仰力矩、减少弹身震动,有利于提高其飞行稳定性及打击精度,可为超声速尾翼弹的改进提供指导。
Previous investigations have shown that an active jet vortex generator can control the flow separation of a supersonic boundary layer effectively, and can be adjusted according to actual situation. In this paper, the jets were mounted at the projectile shoulder of an original standard 122 finned projectile to investigate the flow separation control on the aerodynamic characteristics of the projectile. Numerical simulations were performed with the use of DES method to investigate the supersonic flow fields with and without jets, and the modifications of the boundary layer structures and aerodynamic data for two cases have been compared and discussed. Numerical results show that the jets control can inhibit fluid separation on the surface of a projectile, increase the lift and pitching moment, and reduce the oscillation of projectile body, as a result of improving the flight stability and firing accuracy, which can provide guidance for the improvement of supersonic projectiles.
出处
《工程力学》
EI
CSCD
北大核心
2016年第9期250-256,共7页
Engineering Mechanics
基金
国家自然科学基金项目(11272156)
江苏省研究生科研创新计划项目(KYLX15_0421)
关键词
尾翼弹
射流
边界层分离
稳定性
气动特性
finned projectile
jet
boundary layer separation control
stability
aerodynamic characteristics
