摘要
采用计算流体力学CFD(Computational Fluid Dynam ics)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(Sem i-ImplicitMethod 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.
The flow field and pertormance of a helicopter in common forward thght and forward thght near the ground were analyzed using CFD （computational fluid dynamics） technique. The general governing equa- tions 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 tlme-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-6 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.
出处
《北京航空航天大学学报》
EI
CAS
CSCD
北大核心
2006年第7期751-755,共5页
Journal of Beijing University of Aeronautics and Astronautics
关键词
湍流流动
数值分析
动量源项
壁面函数
turbulent flow
numerical analysis
momentum source term
wall function
