The numerical study of the wake of full-scale slender devices such as aircraft wings and wind turbine blades requires high-fidelity large eddy simulation tools. The broad spectrum of scales involved entails the use of coarse-grain models for the devices. Actuator disk or line methods have been developed for that purpose, and are to date the most employed in that context. These methods transfer the force from the device to the fluid using 3D mollification functions. A novel immersed lifting and dragging line method is here presented, together with its implementation in a hybrid vortex particle-mesh flow solver. The line models the effect of blades or wings on the flow through the generation of vorticity, in a Lagrangian manner. This has several advantages over the treatment inherent to actuator methods: The absence of mollification in the spanwise direction and the relaxation of the classical Courant–Friedrichs–Lewy condition contribute to keeping the accuracy and the efficiency at a high level. The method is thoroughly verified against theory using results on various airfoils and wings. Finally, the efficiency of the approach is illustrated with the simulation of the wake of an elliptical wing. The role of parasitic drag in the development of wake instabilities is pointed out, by comparing configurations with none, moderate and high profile drag. In the last case, the simulation captures the fine scales vortex dynamics and the establishment of a turbulent wake over a length of 30 wing spans.

中文翻译：

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涡流粒子网格法的浸入式提拖线模型

对飞机机翼和风力涡轮机叶片等全尺寸细长设备尾流的数值研究需要高保真大涡流模拟工具。涉及的范围广泛，需要对设备使用粗粒度模型。已经为此目的开发了致动器盘或线方法，并且是迄今为止在该上下文中使用最多的方法。这些方法使用 3D 软化函数将力从设备转移到流体。这里介绍了一种新颖的浸入式提升和拖动线方法，以及它在混合涡流粒子网格流求解器中的实现。这条线以拉格朗日的方式模拟叶片或机翼对涡流产生的影响。与致动器方法固有的处理方法相比，这有几个优点：展向方向没有软化和经典 Courant-Friedrichs-Lewy 条件的松弛有助于将精度和效率保持在高水平。该方法使用各种翼型和机翼的结果与理论进行了彻底的验证。最后，通过对椭圆机翼尾流的模拟来说明该方法的效率。通过比较无、中等和高剖面阻力的配置，指出了寄生阻力在尾流不稳定性发展中的作用。在最后一种情况下，模拟捕获了精细尺度的涡流动力学和 30 个翼展长度上湍流尾流的建立。该方法使用各种翼型和机翼的结果与理论进行了彻底的验证。最后，通过对椭圆机翼尾流的模拟来说明该方法的效率。通过比较无、中等和高剖面阻力的配置，指出了寄生阻力在尾流不稳定性发展中的作用。在最后一种情况下，模拟捕获了精细尺度的涡流动力学和 30 个翼展长度上湍流尾流的建立。该方法使用各种翼型和机翼的结果与理论进行了彻底的验证。最后，通过对椭圆机翼尾流的模拟来说明该方法的效率。通过比较无、中等和高剖面阻力的配置，指出了寄生阻力在尾流不稳定性发展中的作用。在最后一种情况下，模拟捕获了精细尺度的涡流动力学和 30 个翼展长度上湍流尾流的建立。