空化器锥角对超空泡射弹阻力与弹道影响数值研究

Numerical study on the influence of cavitator cone angle on the drag and ballistic of supercavitating projectile

为分析空化器锥角对超空泡射弹减阻效果及运动稳定性的影响规律,基于有限体积法和VOF多相流模型,结合动网格技术构建三维自由尾拍运动仿真模型,以射弹尾部空泡尺寸一致原则设计空化器锥角范围为60°~160°的6种超空泡射弹,比较分析其对减阻效果、尾拍运动特性和弹道特性的影响。结果表明:随着锥角的增大空化器所受阻力先增大后减小,在140°左右所受阻力最大;空化器锥角为60°~100°时射弹以“单侧尾拍”保持稳定,且弹道偏移量较大;空化器锥角为120°~160°时射弹以“双侧尾拍”保持稳定,弹道偏移量小,其中120°锥角的射弹有效射程最大。

Using the finite volume method and the Volume of Fluid(VOF)multiphase flow model,a three-dimensional simulation model is created to examine the impact of the cavitator cone angle on the drag reduction effect and motion stability of supercavitating projectiles.The dynamic mesh approach is used in the model to replicate free tail-slapping motion.According to the principle that the projectile’s tail cavity should always be the same size,six different types of supercavitating projectiles with cavitator cone angles ranging from 60 to 160 are developed.Their effects on drag reduction,tail flap motion characteristics,and ballistic characteristics are compared and analyzed.The findings demonstrate that when the cone angle increases,the cavitator’s resistance first rises and then falls,peaking at about 140;The projectile remains stable with a“one-sided tail-slap”and a significant trajectory offset when the cavitator’s cone angle is between 60 and 100;The projectile is stable with“double tail-slap”and the trajectory offset is minor when the cone angle of the cavitator is between 120 and 160.The projectile with the 120-cone angle has the greatest effective range.