摘要
为了揭示内锥型空心弹关键参数与阻力特性之间的关系,基于30 mm口径内锥型空心弹模型,通过改变锲角和喉径比关键参数,利用计算流体动力学软件Fluent对空心弹在不同马赫数下进行数值仿真,得到了不同参数下的阻力特性。结果表明:在喉径比为0.2时,空心弹会发生阻塞现象,单独增加马赫数不能消除阻塞;消除阻塞前,在同一马赫数条件下,随着喉径比不断增加,阻力系数数值逐渐减小,尤其在阻塞临界点附近,阻力系数数值会出现骤降;消除阻塞后,随着喉径比不断增加,阻力系数数值变化不明显;消除阻塞现象所需马赫数随喉径比增加逐渐减小,喉径比越大越易于消除阻塞问题。锲角的大小对阻力特性影响较大,锲角越大,越易于造成阻塞现象;在喉径比和马赫数相同条件下,锲角越大阻力系数数值越大。在锲角和喉径比相同时,马赫数越大阻力系数值反而越小。在空心弹及类似弹丸设计时,需同时兼顾锲角、喉径比和马赫数对气动特性的影响。
In order to reveal the relationship between the key parameters and resistance characteristics of the inner conical hollow projectile,based on the 30 mm diameter inner conical hollow projectile model,the resistance characteristics of the hollow projectile under different Mach numbers are obtained by changing the key parameters of wedge angle and throat diameter ratio using the computational fluid dynamics software Fluent.The results show that when the throat diameter ratio is too small as 0.2,the hollow projectile will become blocked,and the blocking cannot be eliminated by increasing the Mach number alone.Before removing the obstruction,with the increase of laryngeal diameter ratio,the resistance coefficient value decreases gradually,especially near the critical point of obstruction.After removing the obstruction,the resistance coefficient values did not change significantly with the increase of laryngeal diameter ratio.The Mach number required to eliminate obstruction decreases with the increase of laryngeal diameter ratio.The size of the wedge Angle has a great influence on the resistance characteristics.The larger the wedge Angle is,the easier it is to cause obstruction.Under the condition of the same throat diameter ratio and Mach number,the greater the wedge Angle,the greater the resistance coefficient.When the ratio of wedge angle to throat diameter is the same,the larger the Mach number,the smaller the resistance coefficient value.In the design of hollow projectiles and similar projectiles,the effects of wedge angle,throat diameter ratio and Mach number on aerodynamic characteristics should be considered at the same time.
作者
郑艳军
钟建华
李昌坤
杨慧
ZHENG Yanjun;ZHONG Jianhua;LI Changkun;YANG Hui(Southwest Research Institute of Technology and Engineering,Chongqing 400039,China)
出处
《兵器装备工程学报》
CAS
CSCD
北大核心
2024年第5期52-57,共6页
Journal of Ordnance Equipment Engineering
关键词
内锥型空心弹
阻力系数
仿真
阻塞
锲角
喉径比
internal cone hollow projectile
drag coefficient
numerical simulation
choke
wedge angle
throat diameter ratio
