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首页> 外文期刊>Journal of the American Helicopter Society >Computational Investigation of Micro Hovering Rotor Aerodynamics
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Computational Investigation of Micro Hovering Rotor Aerodynamics

机译：微型悬停转子空气动力学的计算研究

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In this work, a compressible Reynolds-averaged Navier-Stokes code is used to investigate low Reynolds number and low Mach flows, which are typical of micro air vehicles (MAVs). The current work serves as a step toward developing a computational methodology that can serve as a predictive tool for a variety of conventional and unconventional rotary wing MAVs. The performance of unsteady low Mach preconditioning is demonstrated using two-dimensional inviscid isentropic vortex propagation in low Mach number flow. This is followed by extensive validation studies on a micro hovering rotor. The effect of leading and trailing edge geometries is investigated by looking at blunt and sharp profiles and comparing with the experimental data. The thrust and power are reasonably well predicted for all the geometries. Blunt leading edge geometries show poorer performance compared to the corresponding sharp leading edge geometries mainly because of large pressure drag acting at the blunt front. Blunt leading edge geometry also shows a significant leading edge laminar separation bubble, which results in complete separation near the tip. Sharpening the trailing edge shows performance improvement for the blunt leading edge geometry, but not for the sharp leading edge geometry. Flow visualization shows that the tip vortex flow field is very complicated with the presence of secondary vortices and additional vortices formed due to separation near the trailing edge. The tip vortex profiles are reasonably well predicted, but the inadequacy of the turbulence model leads to some discrepancies during tip vortex formation. The swirl velocities for the micro-rotor is found to be significantly larger compared to full-scale rotor, which could be one of the reasons for additional power loss in the smaller scale rotors.
机译：在这项工作中，使用可压缩的雷诺平均Navier-Stokes代码来研究低雷诺数和低马赫流量，这是微型飞行器（MAV）的典型特征。当前的工作是朝着发展一种计算方法学迈出的一步，该计算方法学可以用作各种常规和非常规旋翼MAV的预测工具。在低马赫数流中使用二维无粘性等熵涡流传播来证明非稳态低马赫预处理的性能。接下来是对微型悬停转子的广泛验证研究。通过查看钝角和锋利的轮廓并将其与实验数据进行比较，来研究前缘和后缘几何形状的影响。对于所有几何形状都可以很好地预测推力和功率。相较于相应的锋利的前缘几何形状，钝的前缘几何形状表现出较差的性能，这主要是因为作用在钝的前端的压力拖曳较大。钝的前缘几何形状还显示出明显的前缘层流分离气泡，从而导致尖端附近的完全分离。锐化后缘显示出钝的前缘几何形状的性能改善，但尖锐的前缘几何形状则没有。流动可视化显示，由于存在次级涡旋以及由于后缘附近的分离而形成的附加涡旋，尖端涡旋流场非常复杂。可以很好地预测尖端涡旋的轮廓，但是湍流模型的不足会导致尖端涡旋形成过程中的某些差异。与全尺寸转子相比，发现微转子的旋流速度明显更大，这可能是较小尺寸转子中额外功率损耗的原因之一。

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