摘要
为了研究内锥型空心弹的阻塞现象与入口锥角的关系,仿真研究了入口锥角对空心弹流场的影响。在喉道与入口截面积比为0.6的条件下,基于可压雷诺时均Navier-Stokes(RANS)方程与单方程Spalart-Allmaras(S-A)湍流模型进行研究。对斜坡流场进行数值仿真,并与实验结果对比,验证了该文方法的可行性。采用该文方法模拟了入口锥角分别为10°和30°条件下,空心弹在来流马赫数为2.5时的流场,发现入口锥角是造成气流阻塞的重要影响因素。在来流马赫数为2.5时,利用穷举法计算了入口锥角为10°～30°的流场变化情况,得到空心弹发生阻塞的临界入口锥角为17.8°。计算了空心弹在来流马赫数为2～4时的临界入口锥角,结果表明临界入口锥角随来流马赫数的增大而增大。
The influence of the inlet angleθon the fluid field of an inner conical hollow projectile is simulated to study the relationship between the choking and the inlet angle.In the condition of the area ratio of throat to entrance of 0.6,the research is based on the Reynolds-averaged Navier-Stokes(RANS)equation and the one-equation Spalart-Allmaras(S-A)turbulence model.The numerical simulation of the ramp flow field is carried out and compared with the experimental results,and the accuracy of the method proposed here is verified.Under the condition ofθ=10°andθ=30°,the flow fields of the hollow projectile at Ma=2.5 are simulated by using this method,and the inlet angle is an important factor on the choking of the air flow in projectiles.The flow fields atθ=10°~30°and Ma=2.5 are calculated by using the exhaustive method,and the results show the critical inlet angle of choking isθ0=17.8°.Theθ0 at Ma=2~4 is simulated,and the results showθ0 increases with the increasing Ma.
作者
杜宏宝
蒋锋
黄振贵
陈志华
孙晓晖
Du Hongbao;Jiang Feng;Huang Zhengui;Chen Zhihua;Sun Xiaohui(National Key Laboratory of Transient Physics,Nanjing University of Science and Technology,Nanjing 210094,China;Shanghai Academy of Spaceflight Technology,Shanghai 201109,China;School of Mechanical Engineering,Nanjing University of Science and Technology,Nanjing 210094,China)
出处
《南京理工大学学报》
EI
CAS
CSCD
北大核心
2018年第6期642-646,670,共6页
Journal of Nanjing University of Science and Technology
基金
中央高校基本科研业务费专项资金(30917012101)
关键词
计算流体力学
内锥型空心弹
阻塞
临界入口锥角
穷举法
computational fluid mechanics
inner conical hollow projectile
choke
critical inlet angle
exhaustive method
