Numerical and Experimental Investigations of an Elasto-Flexible Membrane Wing at a Reynolds Number of 280,000
Numerical and Experimental Investigations of an Elasto-Flexible Membrane Wing at a Reynolds Number of 280,000
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雷诺数为 280,000 的弹性柔性膜翼的数值和实验研究
DOI：
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发表时间：
2017
期刊：
影响因子：
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通讯作者：
C. Breitsamter
中科院分区：
文献类型：
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作者：
J. Piquee;C. Breitsamter
本文对雷诺数为280，000的弹性柔性薄膜机翼进行了数值和实验研究。这样的概念有能力适应来流，提供更广泛的飞行包线。在数值研究中可以清楚地观察到这种适应性：翼型的弯度随动压和攻角而变化，这使得失速更加平稳和延迟。从流固耦合（FSI）模拟中得到的数值结果还表明，层流-湍流过渡影响机翼的气动特性，因为它直接影响薄膜上的压力分布和翼型的几何形状。因此，测试了两种不同的湍流模型。此外，实验研究被认为是在本文中估计精度的流固耦合模拟。FSI研究高估了升力系数，而低估了阻力系数，这可以通过模型的动态校准来解释。然而，与热线风速仪系统获得的速度场显示出良好的协议上的模型。薄膜偏转测量值似乎也与FSI模拟的变形翼型的预期几何形状一致。
This work presents numerical and experimental investigations of an elasto-flexible membrane wing at a Reynolds number of 280,000. Such a concept has the capacity to adapt itself to the incoming flow offering a wider range of the flight envelope. This adaptation is clearly observed in the numerical study: the camber of the airfoil changes with the dynamic pressure and the angle of attack, which permits a smoother and delayed stall. The numerical results, obtained from Fluid Structure Interaction (FSI) simulations, also show that the laminar-turbulent transition influences the aerodynamic characteristics of the wing, as it directly affects the pressure distribution on the membrane and the geometry of the airfoil. Two different turbulence models were therefore tested. Furthermore, experimental investigations are considered in this paper to estimate the precision of the FSI simulations. It appears that the FSI study overestimates the lift coefficient, and the drag coefficient is undervalued, which can be explained by dynamic calibration of the model. Nevertheless, the velocity field obtained with the hot-wire anemometry system shows good agreement on the upper side of the model. The membrane deflection measurements also appear to be consistent with the expected geometry of the deformed airfoil from the FSI simulations.