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Simulating unsteady aerodynamics of helicopter rotor with panel/viscous vortex particle method

机译：用面板/粘滞涡旋粒子法模拟直升机旋翼的非定常空气动力学

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The unsteady aerodynamics of a helicopter rotor has been a central issue in the field of rotorcraft aerodynamics. This is because the rotor generates a complex time-dependent pattern of vorticity in its wake, which has significant effects on its performance, stability, loading, and vibration. Conventional free-wake methods used in most of the current comprehensive rotorcraft analysis codes are limited by the potential flow assumption and empirical formulations, such as vortex core size. Based on a numerical solution of the unsteady fluid-dynamic equations governing transportation and diffusion of vorticity, a viscous vortex particle method is coupled with an unsteady panel method to predict the unsteady aerodynamics of helicopter rotor blades with fewer empirical formulations in viscous flow. The coupled method is implemented through the trailing-edge Kutta condition, Neumann boundary condition, and by converting shed-wake doublet panels to wake vorticity. A TreeCode method is also employed to reduce computational cost for practical analysis. Helicopter rotors including the scaled model, Caradonna-Tung, and AH-1G rotors are simulated in hover and forward flight to validate the accuracy of the present approach. The unsteady dynamics of the rotor wake, such as wake contraction, tip-vortex pairing, and vortex roll-up, are well simulated. The predicted inflow distribution is more accurate than that in the conventional free-wake method, and the predicted pressure coefficient distribution and unsteady aerodynamic loads of rotor blades agree well with measured data and computational fluid-dynamics results.
机译：直升机旋翼的不稳定空气动力学一直是旋翼飞行器空气动力学领域的中心问题。这是因为转子在其尾流中会产生复杂的随时间变化的涡度模式，这对转子的性能，稳定性，负载和振动有重大影响。当前大多数旋翼航空器综合分析法典中使用的常规自由苏醒方法均受潜在流量假设和经验公式（例如涡流核心尺寸）的限制。基于控制涡度传输和扩散的非稳态流体动力学方程的数值解，将粘性涡旋粒子法与非稳态面板法相结合，以较少的经验公式来预测直升机旋翼桨叶的非稳态空气动力学。耦合方法是通过后缘Kutta条件，Neumann边界条件以及通过将梭状尾波双重峰面板转换为尾涡来实现的。还使用TreeCode方法来减少实际分析的计算成本。在悬停和向前飞行中模拟了包括比例模型，Caradonna-Tung和AH-1G旋翼在内的直升机旋翼，以验证本方法的准确性。很好地模拟了转子尾流的非稳态动力学，例如尾流收缩，尖端涡流配对和涡旋卷起。预测的入流分布比常规的自由尾流法更准确，并且预测的压力系数分布和动叶片的非定常空气动力学载荷与实测数据和计算流体力学结果非常吻合。

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