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首页> 外文会议>Congress of the International Council of the Aeronautical Sciences; 20060903-08; Hamburg(DE) >EFFECTS OF HELICOPTER ROTOR WAKE CHARACTERISTICS ON BLADE AIRLOADS
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EFFECTS OF HELICOPTER ROTOR WAKE CHARACTERISTICS ON BLADE AIRLOADS

机译：直升机转子尾迹特性对叶片空载的影响

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Several research efforts have been recently conducted, aiming to improve the physical understanding and predictive capabilities of the complicated helicopter rotor flowfield. As a result, advanced mathematical models have been developed, targeting to enhance the aerodynamic computations of rotor wake analysis. The implementation of these mathematical models is presented here, in a developed computational procedure, based on a Lagrangian type, Vortex Element Method. The free vortical wake geometry and rotor airloads are computed. The computational efficiency of special models concerning vorticity diffusion and vortex straining is tested. An investigation regarding the benefit of using curved line segments instead of straight ones, in spite their computational cost, is made with the developed wake relaxation method. The results of curved segments application, combined with concepts engaged for straight segments such as vortex core models, have been computationally evaluated. Investigations have also been performed in order to assess a realistic value for empirical factors included in vorticity diffusion models. The computational results are compared with experimental data from wind tunnel tests, performed during joined European research programs.
机译：最近已经进行了一些研究工作，旨在提高对复杂的直升机旋翼流场的物理理解和预测能力。结果，开发了先进的数学模型，旨在增强转子尾流分析的空气动力学计算。这些数学模型的实现在本文中以拉格朗日类型的涡旋元素方法为基础，在发达的计算过程中进行了介绍。计算了自由涡旋尾流的几何形状和转子的空气负荷。测试了有关涡度扩散和涡旋应变的特殊模型的计算效率。尽管开发了尾流松弛方法，但尽管计算量很大，但仍在研究使用曲线段代替直线段的好处。弯曲段应用的结果与结合直线段的概念（例如涡流核心模型）相结合，已经进行了计算评估。为了评估涡度扩散模型中包含的经验因素的实际价值，还进行了调查。计算结果与参加欧洲研究计划期间进行的风洞试验的实验数据进行了比较。

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