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首页> 外文会议>Congress of the International Council of the Aeronautical Sciences; 20060903-08; Hamburg(DE) >A COUPLED PRESCRIBED WAKE-EULER SOLVER FOR EFFICIENT COMPUTING HELICOPTER ROTOR FLOWS IN HOVER
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A COUPLED PRESCRIBED WAKE-EULER SOLVER FOR EFFICIENT COMPUTING HELICOPTER ROTOR FLOWS IN HOVER

机译：悬停时用于精确计算直升机旋翼流动的预定处方尾气求解器

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摘要

A numerical solution technique is developed to simulate the flowfield of hovering helicopter rotor. The present method uses a coupled prescribed wake-Euler solver to efficiently allow the vortical wake effects. The three-dimensional Euler equations written in a rotating coordinate frame are solved by using a cell-centered finite volume scheme that is based on the Roe's flux-difference splitting on unstructured meshes. High-order accuracy is achieved via the reconstruction of flow variables using the MUSCL interpolation technique. Calculations are carried out for an isolated rotor in hover for two operating conditions of subsonic and transonic tip Mach numbers, M_(tip) = 0.44 and M_(tip) = 0.877, and the collective pitch angle θ_c = 8° (the Caradona and Tung test cases). The computed surface pressure distributions for each case are compared with available numerical and experimental data. The results indicate that for conventional grids, the calculated surface pressure distributions do not agree with the experimental data especially at inboard sections of the blades. This difference may be due to the fact that the numerical methods using course grids have inherent numerical dissipation which can affect the structure of the rotor wake. To improve the computed results, a perturbation method is used and wake effects are modeled using only a tip vortex trailed from the tip of each blade. The resulting surface pressure distributions using the proposed technique exhibit good agreement with the numerical and experimental results, especially for the subsonic case.
机译：开发了一种数值解法技术来模拟悬停直升机旋翼的流场。本方法使用耦合的规定的尾波欧拉求解器以有效地允许涡旋尾波效应。通过使用基于单元格的有限体积方案求解旋转坐标系中编写的三维欧拉方程，该方案基于Roe在非结构化网格上的磁通量差分裂。通过使用MUSCL插值技术重建流量变量，可以实现高阶精度。对于亚音速和跨音速尖端的马赫数M_number，M_（tip）= 0.44和M_（tip）= 0.877，以及总螺距角θ_c= 8°（Caradona和Tung），对悬停的隔离转子进行了计算测试用例）。将每种情况下计算出的表面压力分布与可用的数值和实验数据进行比较。结果表明，对于常规格栅，计算出的表面压力分布与实验数据不一致，尤其是在叶片的内侧部分。这种差异可能是由于以下事实：使用过程网格的数值方法具有固有的数值耗散，这会影响转子尾流的结构。为了改善计算结果，使用了一种摄动方法，并且仅使用从每个叶片的尖端拖尾的尖端涡流对尾流效应进行建模。使用所提出的技术得到的表面压力分布与数值和实验结果具有良好的一致性，特别是在亚音速情况下。

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