带减阻杆的高超声速弹丸气动特性研究  

Research on Aerodynamic Characteristic of the Hypersonic Projectile with Drag-reduction Spike

作　　者：彭磊[1] 王栋[1] 许朋 卓长飞[1] 

机构地区：[1]南京理工大学机械工程学院,南京210094 [2]晋西工业集团有限责任公司技术中心,太原030027

出　　处：《科学技术与工程》2015年第9期142-147,共6页Science Technology and Engineering

摘　　要：为了研究带减阻杆的高超声速弹丸气动特性,基于高精度高分辨率的KFVS气体动力学格式、k-ωSST两方程湍流模型,采用有限体积法求解三维Navier-Stokes方程,并对数值方法的有效性和可靠性进行了验证。在此基础上,对带减阻杆的高超声速弹丸流场进行了数值模拟。研究结果表明:基于高精度高分辨率的KFVS气体动力学格式发展的数值方法可信度较高,能用于弹丸气动特性数值计算;在减阻杆长度一定条件下,随着马赫数的增大,减阻率将提高;在一定的减阻杆长度、马赫数下,随着攻角的增大,全弹总阻力系数、升力系数、俯仰力矩系数将增加;减阻杆基本不会影响弹丸的升力和俯仰力矩。研究结果为高超声速弹丸工程设计提供参考。In order to study the aerodynamic characteristics of hypersonic projectile,the Navier-Stokes equations are solved by finite volume method based on gas kinetic flux splitting scheme and the k-ω SST turbulent flow model,and then the validity and reliability of the numerical methods is verified.On this basis,the flow field of the hypersonic projectile are simulated,The results show that： the development of numerical methods have high reliability based on kinetic flux vector splitting scheme,which can be used for the numerical calculation of the aerodynamic characteristics of projectile; with increasing attack angle,total drag coefficient,left coefficient,pitch moment coefficients increases; drag-reduction spike have no influence on the left and pitch moment of projectile.The results provide a reference for the design of hypersonic projectile.

关 键 词：减阻杆 高超声速弹丸 计算流体力学 气体动力学格式 气动特性 

分 类 号：O354.4[理学—流体力学]