微型旋翼悬停状态气动性能分析方法  

Analysis Method for Prediction of Micro-Rotor Performance in Hover

作　　者：唐正飞[1] 王畅[1] 高卓飞[1] 

机构地区：[1]南京航空航天大学直升机旋翼动力学重点实验室,南京210016

出　　处：《南京航空航天大学学报》2011年第3期357-362,共6页Journal of Nanjing University of Aeronautics & Astronautics

基　　金：航空科学创新基金(2007A52005)资助项目;直升机旋翼动力学重点实验室基金(51463010304ZS5201)资助项目

摘　　要：为了了解微型直升机工作时相关的气动知识,建立了一套微型旋翼悬停状态气动性能分析方法。该方法包含了低雷诺数下微型旋翼桨叶翼型的二维气动特性分析的CFD技术和旋翼气动特性分析的动量/叶素理论。对影响微型旋翼悬停性能的因素做了初步分析,合适的翼型弯曲、桨叶尖削等,有助于提高微型旋翼的最大悬停效率。文中还对分析的部分结果进行了试验验证。In order to better understanding the relevant micro helicopter aerodynamics, a method for the prediction of micro-rotor hover performance is presented.The method combines the computational fluid dynamics（CFD） technique for two-dimensional parametric aerodynamic study of airfoils at low Reynolds numbers with the blade element momentum theory（BEMT） for the prediction of rotor hover performance.The predicted thrust and power of micro-rotor are in good agreement with experimental measurements.The investigation explores the influences of a series of parameters such as airfoil shape and blade plan form on the micro-rotor performance.Theoretical and experimental studies show that thin circular arc airfoil shape,tip tapered geometries and blade plan form with twist distribution will improve the maximum of micro-rotor hover efficiency.

关 键 词：微型旋翼 低雷诺数 悬停性能 动量-叶素理论 CFD方法 

分 类 号：V275.1[航空宇航科学与技术—飞行器设计]