跨声速旋成体弹丸气动力的数值计算  

Computations of Transonic Aerodynamics of Spinning Projectiles

作　　者：乐贵高[1] 马大为[1] 武瑞文[1] 李自勇[1] 于存贵[1] 

机构地区：[1]南京理工大学机械工程学院,南京210094

出　　处：《南京理工大学学报》2003年第6期665-668,共4页Journal of Nanjing University of Science and Technology

摘　　要：用三阶MUSCL TVD格式解三维可压缩流动N-S方程组,湍流模式为Sparlart-Allmaras模型,数值模拟了来流马赫数Ma∞=0.96、攻角α=0°和Ma∞=0.91、攻角α=2°条件下的旋成体弹丸跨声速流场,获得的弹体表面压力系数分布数值结果与实验数据吻合良好。同时还给出了流场的马赫数等值线、弹丸底部流线分布图谱,并对计算的弹底涡流结构作了扼要的分析。The three-dimensional compressible flow Navier-Stokes equations have been solved using the third-order MUSCL type TVD scheme. The Sparlart-Allmaras turbulence model is employed.The flowfield of the spinning projectile under the transonic speed conditions of Ma∞= 0.96 , the angle of attack α=0° and Ma∞= 0.91 , the angle of attack α = 2°is numerically simulated. The results of pressure coefficient distributions on the projectile surface are in agreement with the test data. In addition, the Mach number contours and the streamlines of the projectile base are given. The computed vortex structures in the projectile base are pre-sented and analyzed.

关 键 词：旋成体弹丸 跨声速流 涡 纳维尔-斯托克斯方程 数值模拟 

分 类 号：V211.59[航空宇航科学与技术—航空宇航推进理论与工程] TJ001[兵器科学与技术—兵器发射理论与技术]