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首页> 外文期刊>The ITEA Journal >Highly Accurate Simulations of Low Reynolds Number Micro Air Vehicle Wing Aerodynamics
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Highly Accurate Simulations of Low Reynolds Number Micro Air Vehicle Wing Aerodynamics

机译：低雷诺数微型飞机机翼空气动力学的高精度仿真

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摘要

In this article computations are performed to better understand unsteady, low-Reynolds number aerodynamics, which are critically important in providing insight into the flying characteristics of natural fliers and exploiting natural aerodynamic efficiencies for micro air vehicle (MAV) development. The first computations explore the flow structure over a bio-inspired corrugated airfoil. The flow behavior was found to be strongly affected by the leading-edge geometry due to interaction between the detached shear layer emanating from the leading-edge and first corrugation peak. The second set of simulations explores the aerodynamics of an aspect-ratio, two flexible-membrane wing at angle-of-attack. The impact of membrane flexibility on the aerodynamic performance is shown to come primarily from the development of mean camber, with some further effects arising from the interaction between the dynamic motion of the membrane and the unsteady flowfield above. Finally, the unsteady separation process and induced loading produced by a canonical pitch-and-hold motion for a low-aspect-ratio wing is investigated. The flowfields are computed employing an extensively validated high-fidelity implicit-large-eddy simulation (ILES) approach found to be effective for moderate Reynolds number flows exhibiting mixed laminar, transitional and turbulent regions. This high-order method furnishes a unique, scalable computational capability that has been specifically created to address the simulation issues associated with highly nonlinear, unsteady, transitional flows inherent to MAVs.
机译：在本文中，进行计算是为了更好地理解不稳定的，低雷诺数的空气动力学特性，这对于提供洞察天然飞行器的飞行特性以及为微型飞行器（MAV）开发利用自然空气动力学效率至关重要。首次计算探索了生物启发的波纹翼型上的流动结构。由于从前缘和第一波峰产生的分离的剪切层之间的相互作用，发现流动特性受前缘几何形状的强烈影响。第二组模拟研究了长宽比，两个攻角为柔性膜的机翼的空气动力学特性。膜的柔韧性对空气动力学性能的影响主要来自平均弯度的发展，而膜的动态运动与上方不稳定流场之间的相互作用则产生了一些进一步的影响。最后，研究了低纵横比机翼的非定常分离过程和标准俯仰保持运动产生的感应载荷。使用广泛验证的高保真隐式大涡模拟（ILES）方法计算流场，发现该方法对显示混合层流，过渡和湍流区域的中等雷诺数流有效。这种高阶方法提供了一种独特的，可扩展的计算能力，该能力专门用于解决与MAV固有的高度非线性，不稳定，过渡流相关的仿真问题。

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