论文部分内容阅读
基于κ-ω的SST两方程湍流模型,求解雷诺平均N-S方程获得定常和非定常气动力,耦合翼型弹性振动方程,在时间域内模拟了不同的翼型非定常流动,重点研究了大迎角下的分离流问题,研究结果表明:在百万雷诺数条件下,由于振动引起分离涡的不规律脱落,可能导致气动力平均值的变化;而厚度大于20%的翼型在一定大迎角范围内,会出现分离涡流场平衡态的转化,从流体力学稳定性的角度,解释了风洞实验中大迎角气动力数据的分散性,为大迎角气动力风洞实验的重复性和数据分散性给出了一种新解释.
Based on the κ-ω SST two-equation turbulence model and solving the Reynolds-averaged Navier-Stokes equations, the steady-state and unsteady aerodynamics and coupled airfoil elastic vibration equations are obtained, and different airfoils unsteady flows are simulated in the time domain. Under the condition of millions of Reynolds numbers, the irregular separation of the vortex caused by vibration may lead to the variation of the mean value of the aerodynamic force. However, the airfoil with the thickness greater than 20% The equilibrium state of the separation eddy current field will be transformed. From the perspective of hydrodynamic stability, the dispersion of aerodynamic data at high incidence angle in wind tunnel experiment is explained. Data dispersion gives a new explanation.