基于动态面搭接技术的直升机旋翼流场分析  

Numerical analysis of flow field for helicopter rotors based on dynamic patched grid

作　　者：付炜嘉[1] 李杰[1] 娄琪琳 

机构地区：[1]西北工业大学翼型叶栅空气动力学国防科技重点实验室,西安710072

出　　处：《应用力学学报》2014年第3期311-316,483,共6页Chinese Journal of Applied Mechanics

基　　金：国家自然科学基金(90816027;1117240;10772148)

摘　　要：为了进一步提高直升机旋翼流场计算的精度与效率,本文根据直升机旋翼的运动特点,发展了一种基于结构化网格动态面搭接技术及低速预处理技术的直升机旋翼流场的非定常数值分析方法。采用该方法分别对Caradonna-Tung、UH-60A旋翼模型的悬停流场及NASA某旋翼无升力前飞流场进行了数值分析;将计算所得的旋翼表面压力分布与风洞试验结果进行了对比,对旋翼的尾涡结构进行了相关分析。分析结果表明:本文所发展的方法具有较高的精度且计算速度快,并能够比较准确地捕捉直升机旋翼的尾涡结构,可以用于直升机旋翼流场的分析研究,从而为开展考虑挥舞及变距运动的直升机旋翼前飞状态非定常气动特性的研究奠定了基础。The helicopter rotor aerodynamics is the focus study of computational fluid dynamics. In order to improve the efficiency and the accuracy of the numerical analysis, in this paper, according to the characteristics of helicopter rotor flow field, a method based on structured dynamic patched grid technology and low speed precondition is developed to analyze the unsteady flow filed of helicopter rotor. Applications are made to the hovering flow field of Caradonna-Tung and UH-60A rotor model and the forward flight flow field of the NASA none lift rotor model. The numerical results are also presented to compare with the wind tests results. The analysis shows that the method developed in this paper is accurate, reliable, and be able to accurately capture the helicopter rotor wake vortex structure, it can be used for helicopter rotor flow field analysis. This paper lays a foundation for analyze the forward flight flow field of helicopter rotor consider wave and pitch movement.

关 键 词：动态面搭接 直升机旋翼 数值分析 旋翼流场 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]