论文部分内容阅读
当今,求解飞行器扰流数学模型方程具有迫切的现实意义。在设计飞机机体部件或者航空发动机时,广泛应用数值模拟方法。本文在Spalart-Allmaras,k-ξ、k-w-sst、Transition SST湍流模型基础上建立了二维流动的数学模型,利用Ansys ICEM-Fuent软件模拟了低雷诺数条件下(Re=3500000、Re=6000000、Re=8000000)型NACA-0012和NACA-0006翼型在不同攻角(0°~20°)的二维湍流流动,生成翼型的升力系数Суа及静压力分布云图,并将其结果与实验数值和其他作者的数值实验相比较,进一步验证了数值模拟计算结果的可信度,可将其进一步应用到低速飞行器的启动计算中。
Nowadays, it is of urgent practical significance to solve mathematical equations of aircraft turbulence. In the design of aircraft body parts or aero-engines, numerical methods are widely used. Based on the Spalart-Allmaras, k-ξ, kw-sst and Transition SST turbulence models, a mathematical model of two-dimensional flow is established in this paper. Ansys ICEM-Fuent software is used to simulate the low Reynolds number conditions , Re = 8000000) Two-dimensional turbulent flows of NACA-0012 and NACA-0006 airfoils at different angles of attack (0 ° ~ 20 °) were used to generate airfoil lift coefficient Суа and static pressure distribution cloud chart, Compared with the numerical experiments of other authors, the experimental data further verify the reliability of the numerical simulation results and can be further applied to the startup calculation of low-speed aircraft.