北京航空航天大学学报 ›› 2006, Vol. 32 ›› Issue (07): 751-755.

• 论文 •    下一篇

前飞旋翼三维湍流场的数值模拟

于子文, 曹义华   

  1. 北京航空航天大学 航空科学与工程学院, 北京 100083
  • 收稿日期:2005-08-19 出版日期:2006-07-31 发布日期:2010-09-19
  • 作者简介:于子文(1977-),男,黑龙江齐齐哈尔人,博士生, zhaoliqie@163.com.

Three dimensional turbulence numerical simulation of rotor in forward flight

Yu Ziwen, Cao Yihua   

  1. School of Aeronautic Science and Technology, Beijing University of Aeronautics and Astronautics, Beijing 100083, China
  • Received:2005-08-19 Online:2006-07-31 Published:2010-09-19

摘要: 采用计算流体力学CFD(Computational Fluid Dynamics)方法,分析正常前飞和近地前飞时直升机的流场与性能.在直角坐标系中,采用有限体积法和压力耦合方程的半隐式法SIMPLER(Semi-Implicit Method for Pressure-Linked Equations Revised)算法求解三维定常不可压的湍流N-S(Navier-Stokes)方程.在分析中,旋转的螺桨被描绘成沿螺桨桨叶展向分布、与本地流动参数相关以及时间平均的动量源项.计算方法还包括K-ε湍流模型和壁面函数法等措施.流场分析和性能预测同实验测量数据的良好的一致性表明,这种CFD方法可以有效的分析直升机的具体设计问题.

Abstract: The flow field and performance of a helicopter in common forward flight and forward flight near the ground were analyzed using CFD (computational fluid dynamics) technique. The general governing equations of turbulent flow were set up, and were directly solved by finite volume method and SIMPLER (semi-implicit method for pressure-linked equations revised) approach in Cartesian coordinates. The spinning rotor was represented as time-averaged momentum source terms distributed along the span of the rotor with functional relationship to the local flow conditions in N-S(Navier-Stokes) equations. K-ε turbulence model and wall function method were included in the calculation method. The calculated results for flow field and performance correlation show good agreement with the measured data. Therefore, the numerical simulation technique is proved to be feasible for analyzing design issues of a helicopter.

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