摘要
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。
In this paper, the dynamic process of an oscillating airfoil over viscous flow were numerically simulated,The Navier-Stokes equations were solved by the implicit factorized finite difference algorithm with Bald-win-Lomax turbulent model. The numerical results have shown that.(l) the shock wave strength and its location are nonlinear response to the motion of the airfoil, (2) oscillation of the airfoil can control the separation and augment the lift force, (3) the characteristics of lift loop is determined by the incidence of the airfoil and the amplitude of oscillation.
出处
《空气动力学学报》
CSCD
北大核心
1993年第2期143-148,共6页
Acta Aerodynamica Sinica
关键词
振动翼型
激波
分离
数值模拟
oscillating airfoil, shock wave, separation, numerical simulation.
