摘要
基于Navier-Stokes方程和单方程The Spalart-Allmaras湍流模型对低阻空心弹的超声速流场进行了数值模拟。模型求解技术包括用有限体积法进行空间离散,AUSM格式进行对流项离散,并采用网格自适应加密技术来提高对激波间断的分辩。得到了空心弹超声速湍流飞行条件下的复杂波系结构与阻力特性曲线,并讨论了空心弹在不同攻角与马赫数情况下的飞行特性。
Based on the Navier-Stokes equation and the turbulence model of single Spalart-Allmaras equation,the flow field of a low-drag hollow projectile was simulated numerically.The solution technology for above equations including the finite volume method for discretion of space terms,AUSM scheme was employed for the solution of convection terms and the adaptive mesh refinement technology was used to improve the resolution for the shock wave capture.The complicated shock wave structures and the drag curves were obtained,furthermore,the flight characteristics of the hollow projectile with different Mach numbers and attack angles were discussed.
出处
《弹箭与制导学报》
CSCD
北大核心
2011年第4期73-75,共3页
Journal of Projectiles,Rockets,Missiles and Guidance
基金
国防科技重点实验室基金资助
关键词
空心弹
空气阻力
湍流
hollow projectile
drag force
turbulence
