内锥型空心弹阻塞喉径面积比的仿真研究  

Simulation Research on Critical Area Ratio of Throat to Entrance of Inner Conical Hollow Projectile Under Choke Flow

作　　者：全鑫 张红艳 马铁华[1,3] 张瑜 武耀艳[1,3] QUAN Xin;ZHANG Hongyan;MA Tiehua;ZHANG Yu;WU Yaoyan(School of Electrical and Control Engineering,Taiyuan 030051,China;School of Science,Taiyuan 030051,China;National Key Laboratory for Electronic Measurement Technology,Taiyuan 030051,China)

机构地区：[1]中北大学电气与控制工程学院,太原030051 [2]中北大学理学院,太原030051 [3]中北大学电子测试技术国家级重点实验室,太原030051

出　　处：《兵器装备工程学报》2021年第4期97-101,共5页Journal of Ordnance Equipment Engineering

基　　金：装备预研重点实验室基金项目(6142001180408)。

摘　　要：为了研究内锥型空心弹喉径面积之比与阻塞现象发生的关系,给空心弹的设计优化提供参考,基于可压雷诺时均Navier-Stokes方程与Spalart-Allmaras湍流模型,对入口锥角为12°的某型空心弹丸的流场进行了数值模拟。在来流Ma=2.5的流场中,保证弹丸其他几何参数相同的情况下,喉径面积比为0.4时空心弹发生了阻塞现象,喉径面积比为0.8时未发生阻塞,表明喉径面积之比是影响空心弹发生阻塞的重要因素。为得到空心弹的阻塞临界喉径面积比,利用穷举法计算得到了不同喉径面积比的空心弹流场,结果发现:同一空心弹丸在不同Ma下的阻塞临界喉径面积比不同,Ma=2.0时,空心弹的阻塞临界喉径面积比为0.701;Ma=2.5时为0.504;Ma=3.0时为0.372;Ma=3.5时为0.287;Ma=4.0时为0.226,Ma与阻塞临界喉径面积比成反比例关系。同一空心弹丸在不同Ma下,阻力系数随喉径面积比变化的趋势相似,流场变化过程相似。阻塞前阻近似力系数随喉径面积比的减小几乎不变;阻塞时,阻力系数突跃性增大;阻塞后,阻力系数随喉径面积比的减小而增大。In order to study the relationship between the area ratio of throat to entrance and the choking,providing reference for the design and optimization,a numerical simulation of an inner conical hollow projectile was carried out.In the condition of the inlet angle of 12°,the research was based on the Reynolds-averaged Navier-Stokes equation and the Spalart-Allmaras turbulence model.In the flow field at Ma=2.5,under the condition of the other geometric parameters of the projectile which are the same,different simulation results indicated that the area ratio of throat to entrance is an important factor on the choking of the air flow in projectiles.In order to obtain the critical area ratio of throat to entrance of inner conical hollow projectile under choke flow,the exhaustive method was carried out to calculate and list the flow fields with different area ratio of throat to entrance.The results showed that the same hollow projectile has different critical area ratio of throat to entrance under choke flow at different Ma.When Ma=2.0,the critical area ratio of throat to entrance of hollow projectile under choke flow is 0.701;when Ma=2.5,it is 0.504;when Ma=3.0,it is 0.372;when Ma=3.5,it is 0.287;when Ma=4.0,it is 0.226.Ma is inversely proportional to the critical area ratio of throat to entrance.For the same hollow projectile under different Ma,the change trend of the drag coefficient with the area ratio of throat to entrance is similar,and the flow field change process is similar.The drag coefficient before the choking is almost unchanged with the decrease of the area ratio of throat to entrance.When the choking occurs,the drag coefficient increases abruptly.After the choked,the drag coefficient increases with the decrease of the area ratio of throat to entrance.

关 键 词：内锥型空心弹 计算流体力学 阻塞现象 喉道面积 入口面积 穷举法 阻力系数 

分 类 号：TJ011.2[兵器科学与技术—兵器发射理论与技术]