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本文直接从N-S方程出发,利用LU-ADI格式和Baldwin-Lomax代数湍流模型研究了粘性流绕俯仰振动翼型的流动。数值实验表明,本文的数值结果同实验吻合较好。通过数值模拟手段研究了振动对流场中激波和分离这两大主要特征的影响,结果发现;(1)激波滞后于攻角的变化,如当NACA0012翼型在负攻角状态下上翼面存在激波而下翼面无激波。(2)由于翼型的振动,分离被减轻升力相对提高。(3)随翼型攻角和振幅的变化,翼型振动的升力回线走向可不同。
Based on the N-S equation, the LU-ADI format and the Baldwin-Lomax algebraic turbulence model are used to study the flow of viscous flow around pitch vibration airfoils. Numerical experiments show that the numerical results in this paper are in good agreement with experiments. The results show that: (1) The shock lags behind the change of the angle of attack, such as when the NACA0012 airfoil at a negative angle of attack There is a shock on the airfoil but no shock on the airfoil. (2) Due to the vibration of the airfoil, the separation is relieved of the relative increase in lift. (3) With the change of airfoil angle of attack and amplitude, the lift loop of airfoil vibration may be different.