并列平头尾翼弹气动干扰特性计算研究  

Computational study on aerodynamic interactions between two parallel flat-head projectile with tail

作　　者：陈志宏 谭献忠[1] 吕续舰 CHEN Zhihong;TAN Xianzhong;LYU Xujian(School of Energy and Power Engineering,Nanjing University of Science and Technology,Nanjing 210094,China)

机构地区：[1]南京理工大学能源与动力工程学院,南京210094

出　　处：《兵器装备工程学报》2022年第10期96-105,共10页Journal of Ordnance Equipment Engineering

基　　金：国家重点实验室基金项目(6142604190302)。

摘　　要：采用数值方法研究并列尾翼弹不同间隙比下的流动特性和流场空间结构。计算结果表明:当Ma=1.765、α=4°时,存在临界间隙比G_(cr)=2.75、5.5、7,使得间隙比对轴向力系数的气动干扰效应不再显著;不同间隙比下2弹激波与膨胀波多波系相互干扰的综合影响,使得2弹表现出不同的“吸引”-“排斥”状态和偏航转动特性;在G=1.5时,弹头和尾翼部分激波干扰形成高压区,弹身内侧膨胀波干扰形成低压区,2弹尾翼后产生对称尾涡,流线呈现相互“吸引”状态;在G=10时,间隙比对该工况下的气动特性干扰效应不再显著。Numerical methods were used to study the flow characteristics and the spatial structure of the flow field under different clearance ratios of the parallel tail projectiles. The results show that when Ma=1.765 and α=4°, there are different critical gap ratios G_(cr)=2.75, 5.5, 7, so that the aerodynamic interference effect of the gap ratio on the axial force coefficient is no longer significant;The combined effect of the mutual interference of the shock wave and the expansion wave of the two bombs under different clearance ratios makes the two bombs show different “attractive” and “repulsive” states and yaw characteristics;When G=1.5, shock wave interference of warhead and tail wing forms high pressure area. The expansion wave on the inside of the projectile interferes to forms a low pressure area. A Symmetrical tail vortex was produced behind the two projectiles, and the streamlines are in a state of mutual “attraction”. When G=10, the clearance ratio is no longer significant for the interference effect of the aerodynamic characteristics under this working condition.

关 键 词：并列 激波 间隙比 数值模拟 气动干扰 

分 类 号：TJ011[兵器科学与技术—兵器发射理论与技术]