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首页> 外文期刊>Bulletin of the American Physical Society >APS -70th Annual Meeting of the APS Division of Fluid Dynamics- Event - Airfoil stall interpreted through linear stability analysis
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APS -70th Annual Meeting of the APS Division of Fluid Dynamics- Event - Airfoil stall interpreted through linear stability analysis

机译：APS-流体动力学APS部门第70届年会-事件-通过线性稳定性分析解释机翼失速

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Although airfoil stall has been widely investigated, the origin of this phenomenon, which manifests as a sudden drop of lift, is still not clearly understood. In the specific case of static stall, multiple steady solutions have been identified experimentally and numerically around the stall angle. We are interested here in investigating the stability of these steady solutions so as to first model and then control the dynamics. The study is performed on a 2D helicopter blade airfoil OA209 at low Mach number, $Msim0.2$ and high Reynolds number, $Resim1.8 imes 10^6$.Steady RANS computation using a Spalart-Allmaras model is coupled with continuation methods (pseudo-arclength and Newton's method) to obtain steady states for several angles of incidence. The results show one upper branch (high lift), one lower branch (low lift) connected by a middle branch, characterizing an hysteresis phenomenon.A linear stability analysis performed around these equilibrium states highlights a mode responsible for stall, which starts with a low frequency oscillation. A bifurcation scenario is deduced from the behaviour of this mode. To shed light on the nonlinear behavior, a low order nonlinear model is created with the same linear stability behavior as that observed for that airfoil.
机译：尽管机翼失速已得到广泛研究，但这种现象的根源表现为升力突然下降，至今仍不清楚。在静态失速的特定情况下，已在失速角附近通过实验和数值方法确定了多个稳态解。我们在这里有兴趣研究这些稳定解决方案的稳定性，以便首先建模然后控制动力学。该研究是在低马赫数$ Msim0.2 $和高雷诺数$ Resim1.8 imes 10 ^ 6 $的2D直升机叶片翼型OA209上进行的。使用Spalart-Allmaras模型的稳定RANS计算与连续方法相结合（伪弧长和牛顿法）获得几个入射角的稳态。结果表明，一个上部分支（高升程），一个下部分支（低升程）由中间分支连接，表现出磁滞现象。围绕这些平衡状态进行的线性稳定性分析强调了一种导致失速的模式，该模式以低速开始频率振荡。从该模式的行为推论出分叉情形。为了阐明非线性行为，创建了一个低阶非线性模型，该模型具有与该机翼相同的线性稳定性。

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