旋转尾翼弹马格努斯效应数值模拟  

Numerical Investigation on Magnus Effect for Rotation Fin-stabilized Projectile

作　　者：吴放 王学德[1] 常思江[1] 刘士杰 WU Fang;WANG Xuede;CHANG Sijiang;LIU Shijie(School of Energy and Power Engineering,Nanjing University of Science and Technology,Nanjing 210094,China;The Second Scientific Research Department,Northwest Industrial Group Corporation,Xi’an 710043,China)

机构地区：[1]南京理工大学能源与动力工程学院,江苏南京210094 [2]西北工业集团有限公司科研二所,陕西西安710043

出　　处：《弹道学报》2018年第1期12-18,共7页Journal of Ballistics

基　　金：国家自然科学基金项目(11402117);中国博士后科学基金项目(2013M541676)

摘　　要：为研究低速旋转尾翼稳定弹箭的马格努斯效应,采用滑移网格技术,在超声速条件下对某低旋尾翼弹开展了气动数值模拟。对弹箭绕弹轴自旋的流场进行非定常计算,获得了该弹箭的气动系数;对马格努斯效应在不同工况下的变化规律进行了理论分析,讨论了不同因素对马格努斯效应产生的影响。结果表明,相同转速下,旋转尾翼弹的马格努斯效应随攻角增加而增大,且在40°~60°攻角范围内达到峰值;对于相同攻角,马格努斯力和力矩系数在较大转速下呈线性增加趋势。To study the Magnus effect of low-speed rotation fin-stabilized projectile(FSP),the aerial numerical simulation of a low-rotation finned missile under supersonic conditions was carried out based on the sliding mesh.The flow-field of FSP rotating round projectile axis was simulated by unsteady computation,and the aerodynamic coefficients of the missile were obtained.The change rule of the Magnus force and the moment coefficient under different working conditions was analyzed theoretically.The influence of different factors on the Magnus effect was discussed.The numerical results show that the Magnus effect of the rotation FSP increases with the increase of attack angle at the same speed,and reaches the peak in the range of 40°to 60°.For the same attack angle,the Magnus force and its moment coefficient increase linearly with the change of speed at large rotation-rate.

关 键 词：尾翼稳定弹 马格努斯效应 计算流体力学 数值模拟 

分 类 号：TJ013.2[兵器科学与技术—兵器发射理论与技术]