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Challenges in the aerodynamics modeling of an oscillating and translating airfoil at large incidence angles

机译：大入射角振荡和平移翼型的空气动力学建模面临的挑战

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摘要

The challenges in the modeling of the unsteady lift of a two-dimensional NACA 0012 airfoil oscillating and translating at large incidence angles are investigated in this paper. Forced oscillation motions with two reduced frequency values of 0.1 and 1.0 were used. The CFD results show that a hysteresis loop was developed in the lift variation with angle of attack; shapes of the loops change significantly with reduced frequency value. A dynamic stall vortex was identified in the pitching and plunging motions with k = OA. This vortex delays the onset of flow separation over the upper surface to a higher incidence than would occur in steady conditions. The unsteady lift of the very fast motion is enhanced significantly due to the formation of a compression wave on the lower surface and an expansion wave on the upper surface. The results show clear limitations of unsteady aerodynamic theories for modeling motions at high incidences. Also, the CFD solution of indicial functions show a large oscillation at angles of attack beyond the stall angle, but the predictions of a model based on Radial Basis Function matches CFD values quite well.
机译：本文研究了二维NACA 0012机翼在大入射角下振荡和平移时非定常升力的建模挑战。使用了两个减小的频率值0.1和1.0的强制振荡运动。 CFD结果表明，在随迎角变化的升程变化中产生了磁滞回线。环路的形状随着频率值的降低而发生显着变化。在k = OA的俯仰和俯冲运动中发现了动态失速涡。与在稳定条件下发生的涡流相比，该涡流将上表面的流分离的发生延迟到更高的发生率。由于在下表面形成了压缩波，在上表面形成了膨胀波，因此，非常快运动的不稳定提升得到了显着增强。结果表明，不稳定的空气动力学理论对高发运动建模具有明显的局限性。此外，独立函数的CFD解决方案在迎角超过失速角时显示出较大的振荡，但是基于径向基函数的模型预测与CFD值非常匹配。

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