基于Fluent的亚音速翼型气动特性数值研究

Numerical Study on Subsonic Airfoil Aerodynamic Characteristics Based on the Fluent

根据Spalart-Allmaras模型建立了NACA0006翼型二维湍流流动模型,并对模型近壁面进行了网格加密处理.利用Fluent软件模拟了NACA0006翼型的二维湍流流动,得到在不同攻角及马赫数下升力系数和阻力系数的变化特性.研究结果表明,在所选攻角范围内,随着攻角的增大,升力系数和阻力系数均逐渐增大;在跨音速区,由于激波的产生,升力系数急剧下降.Fluent为研究翼型气动特性提供了重要参考和依据.

Modeling 2D Turbulence Model of NACA0006 airfoil according to the Spallart-Allmaras,and to the wall near the grid is encrypted.Using Fluent software simulate the NACA0006 airfoil 2d turbulent flow.The lift coefficient and the resistance coefficient Variation characteristics in the different Aangle of attack and Mach number are got.The results show that,in the different Angle of attack and Mach number,with attack Angle increasing lift coefficient and resistance coefficients are increased gradually.Sonic area in cross,due to shock wave formation,lift coefficient decreasing sharply.And Fluent airfoil aerodynamic characteristics for research provides important reference and basis.