翼形参数对某弹道修正迫弹气动特性的影响  

Effect of Airfoil Parameters on Aerodynamic Characteristics of Trajectory-correction Mortar Projectile

作　　者：沈皓敏 杨新民[1] 

机构地区：[1]南京理工大学瞬态物理国家重点实验室,江苏南京210094

出　　处：《弹道学报》2017年第3期32-37,55,共7页Journal of Ballistics

摘　　要：为研究不同翼形几何参数对某弹道修正迫弹流场特性和气动特性的影响,基于3D N-S方程和S-A湍流模型,对不同翼形结构的弹丸流场进行模拟,得到了不同翼形几何参数下的弹丸在平衡攻角时的升力系数和稳定储备量。仿真结果表明:翼型弯度越大,升力系数越大,稳定储备量呈先增加后减小的趋势;头部舵翼的安装位置不宜过于靠后;舵翼展长越大,升力系数越大,稳定储备量越小;尾翼根弦长度越大,升力系数越大,稳定储备量先增加后减小。To investigate the effect of airfoil geometry parameters on flow field characteristics and aerodynamic characteristics of trajectory correction mortar projectile, the 3-dimensional N-S equations and S-A（ Spalart- Allmaras） turbulence model were used to simulate the flow field of projectiles with different airfoil geometry parameters. The lift coefficient at the balanced attack angle and margin of stability were obtained. The results show that the greater the canard camber, the more the lift coefficient, and the margin of stability increases first and then decreases. The installation location of canard should not be too far back. The greater the canard wingspan, the more the lift coefficient and the less the margin of stability. The greater the tail root chord length, the more the lift coefficient, and the margin of stability increases first and then decreases.

关 键 词：弹道修正 翼形几何参数 流场仿真 升力系数 稳定储备量 

分 类 号：TJ303.4[兵器科学与技术—火炮、自动武器与弹药工程]