弹箭尾翼气动减阻方法研究
Researchon Aerodynamic Drag Reduction Method of Fin-Stabilized Projectile
杨宝清 1张龙 1姚新涛 1肖阳2
作者信息
- 1. 西北机电工程研究所, 陕西 咸阳 712099
- 2. 93428 部队, 河北 保定 071051
- 折叠
摘要
为了增大尾翼弹弹道射程和打击范围,利用气动仿真与外弹道仿真计算相结合,分析了尾翼后掠角和斜切角对气动特性和弹道特性的影响.针对某六尾尾翼弹,利用气动仿真分析了后掠角和尾翼斜切角对阻力、升力、静稳定性和弹道特性的影响.仿真结果表明,尾翼产生的阻力占比较大,在一定范围内加大尾翼后掠角可有效减阻.当尾翼斜切角较小时,增大后掠角提高升力和静稳定性;当尾翼斜切角较大时,增大后掠角不一定可以提高升力和静稳定性.综合设计尾翼斜切角和后掠角以达到减阻效果时,需考虑尾翼前缘面积和迎风面与来流夹角.算例结果表明:40°尾翼后掠角和10°尾翼斜切角组合优化的条件下,阻力减小到原来的60%,最大射高提高了30%,射程提高了40%.
Abstract
In order to increase the range and striking range of fin-stabilized projectiles,the effects of sweepback angle and oblique angle on aerodynamic and trajectory characteristics were studied by aero-dynamic simulation and trajectory simulation calculation.For a fin-stabilized projectile with six tail fins,the effects of the sweepback angle and oblique angle on drag,lift,static stability and trajectory characteristics were analyzed by aerodynamic simulation.The results show that the drag is greatly af-fected by the configuration of tail fins,and the drag can be reduced effectively by increasing the sweep-back angle to a certain extent.When the oblique angle is small,the lift and static stability can be im-proved by increasing the sweepback angle.However,when the oblique angle is large,the lift and static stability may not necessarily be improved by increasing the sweepback angle.The area of the leading edge of tail fins and angle between the windward side and incoming flow should be considered when re-fining the sweepback angle and oblique angle to reduce the drag.The simulations show that the drag is reduced to 60%,the maximum firing height is increased by 30%and the range is increased by 40%under the 40° sweepback angle and 10° oblique angle.
关键词
气动仿真/尾翼优化/后掠角/斜切角/外弹道计算Key words
CFD/tail layout optimization/sweep angle/tail oblique angle/trajectory simulation引用本文复制引用
出版年
2024
NETL
NSTL
万方数据