摘要
该文采用有限体积法数值离散雷诺时均Navier-Stokes方程,模拟了超声速飞行的圆柱体外部流场。其中两种湍流模式,即Spalart-A llmaras湍流模型和RNGk-ε湍流模型分别应用于该问题的求解。文中给出了数学模型和计算结果,并与实验数据进行了比较。结果表明:采用Spalart-Allmaras湍流模型能很好地描述高速运动体复杂的外部流场。利用上述模型对超声速飞行的底部排气弹三维流场进行数值研究,计算结果揭示了流场的物理现象和基本规律,以期对底部排气弹设计提供理论指导。
A 3-D turbulent outer flow field of the supersonic flying cylinder flow is simulated numerically through Reynolds-averaged Navier-Stokes equations differentiated by the finite volume method. Two turbulence models which include a Spalart-Allmaras model and a RNG k-ε model are utilized to solve this problem separately. The mathematic models and the computed results are given. Compared with the experimental data, it is shown that the Spalart-Allmaras model performs much better in simulating outer flow fields for supersonic flying body. Based on the Spalart-Allmaras model, the paper also presents a 3-D numerical investigation for flow fields of supersonic flying base bleed projectile. The numerical study reveals the physical phenomenon and the basic rule of flow fields.
出处
《南京理工大学学报》
EI
CAS
CSCD
北大核心
2007年第1期27-30,共4页
Journal of Nanjing University of Science and Technology
关键词
底部排气弹
湍流模型
超声速
base bleed projectile
turbulent model
supersound
