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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.
Based on the Spalart-Allmaras model, a two-dimensional turbulent flow model of NACA0006 airfoil was established and the near wall of the model was encrypted by using a mesh.Using Fluent software to simulate the two-dimensional turbulent flow of NACA0006 airfoil, Down force coefficient and drag coefficient.The results show that the lift coefficient and the drag coefficient increase with the increase of the angle of attack in the selected angle of attack, , The lift coefficient drops sharply.Fluent provides an important reference and basis for the study of aerodynamic characteristics of airfoils.