超声速飞行底部排气弹三维湍流流场数值模拟

Numerical Inwestigation of 3-D Turbulet Flow Fields for Supersonic Flying Base Bleed Projectile

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.