机动弹头高超声速粘性绕流数值模拟  

Numerical Simulation of Hypersonic Viscous Flows Over Maneuvering Missile

作　　者：刘伟[1] 

机构地区：[1]国防科技大学航天与材料工程学院,长沙410073

出　　处：《力学季刊》2001年第4期428-432,共5页Chinese Quarterly of Mechanics

摘　　要：采用空间二阶精度的交替方向隐式分解的NND格式求解完全气体假定下的非定常薄层近似Navier-Stokes方程,并采用抛物化的椭圆型方程生成复杂带翼弹头的空间网格。最后给出了机动弹头在M_∞=7.3,α=20°下的流场计算结果。计算结果表明:本文所采用的计算网格及计算方法可以适用于高超声速复杂流场的数值模拟。Under the assumption of perfect gas, the TLNS equations were solved by alternating direction implicit NND scheme, and the space grids of complex wing-shape were generated by solving parabolic partial differential equations. Finally, the numerical simulation results of maneuvering missile were shown under the conditions: M∞ = 7.3, α = 20°. The results show that the grid and the method which are developed in this paper can be used in numerical simulation of hypersonic complex flows.

关 键 词：机动弹头 高超音速流动 数值模拟 Navier-Stokes方程 粘性绕流 隐式分解 NND格式 完全气体 网格 高超音速空气动力学 计算流体力学 

分 类 号：V211.4[航空宇航科学与技术—航空宇航推进理论与工程] O354.4[理学—流体力学]