摘要
为研究带尾翼超空泡射弹在跨音速运动过程中空泡发展特性和阻力特性,本文利用CFD仿真软件,基于简化的Rayleigh-Plesset空化模型、SST湍流模型、Tait液体状态方程建立了考虑可压缩超空化流场的数值模型,通过与文献[7]试验结果进行对比,完成了数值模型的校验,并计算了跨音速运动马赫数为0.7~1.05速度区间内的超空化流场。计算结果表明:由于尾翼的存在,使得射弹尾部出现涡流现象,且随速度的增大而增强;跨音速过程中,由于激波的作用,空泡尺度受到强烈的压缩,尾翼最先出现沾湿,形成带有凸起的空泡形态;射弹阻力系数随着速度的增加而增大,接近音速时,出现剧烈陡增,尾翼阻力占比增加,受到的冲击压强量级最高可达102 MPa。
In order to study the development and drag characteristics of supercavitating projectiles with fins in transonic motion,a numerical model considering compressible supercavitation flow field was established by using CFD simulation software based on simplified Rayleigh-Plesset cavitation model,SST turbulence model and Tait liquid state equation.Compared with the experimental results in Ref.[7],the numerical model was verified and the supercavitation flow field in the transonic motion region at Mach number between 0.7 and 1.05 was calculated.The simulated results showed that because of the presence of the tail,vortex phenomenon was observed at the rear of the projectile and enhanced with the increase of speed;In the transonic motion,owing to the action of shock wave,the bubble scale near the projectile body was strongly compressed,and the fins were the earliest wetted to form a cavity with bulged shape;The drag coefficient of projectile increased with the increase of velocity.When approaching the speed of sound,it increased sharply and the proportion of tail drag increased.The maximum impact pressure can reach 100 MPa.
作者
王瑞
党建军
姚忠
祁晓斌
WANG Rui;DANG Jian-jun;YAO Zhong;QI Xiao-bin(College of Marine Engineering,Northwestern Polytechnical University,Xi’an 710072,China;Northwest Institute of Mechanical&Electrical Engineering,Xianyang 712099,China)
出处
《船舶力学》
EI
CSCD
北大核心
2019年第10期1160-1167,共8页
Journal of Ship Mechanics
基金
青年托举工程项目（2016QRNC001）
关键词
兵器科学与技术
空泡形态
跨音速运动
水动力
尾翼
ordnance science and technology
cavity morphology
transonic motion
hydrodynamic
fins
