南京航空航天大学学报（英文版）2021，Vol.38Issue(z1)：10-16,7.
基于前缘下垂的提升旋翼悬停气动特性研究
Research on Aerodynamic Characteristics of Hovering Rotor Based on Leading Edge Droop
摘要
Abstract
In view of the reduction of hovering efficiency near high tension when a helicopter rotor hovers,a numerical simulation method of lifting rotor hovering aerodynamic characteristics based on leading edge droop is established in this paper. It is dominated by Reynolds average N-S equation in integral form. Firstly,VR-12 airfoil is taken as the research object,and the influence of leading edge droop angle on the aerodynamic characteristics of two-dimensional airfoil is studied. Secondly,the modified 7A rotor is taken as the research object,and the effects of different leading edge droop angles at the position of blade r/R=0.75—1 on the aerodynamic characteristics in hover are explored. It is found that the leading edge droop can significantly improve the aerodynamic characteristics of two-dimensional airfoil and three-dimensional hovering rotor near high angle of attack,and can effectively inhibit the generation of stall vortex.关键词
直升机旋翼/悬停/前缘下垂/气动特性Key words
helicopter rotor/hovering/leading edge droop/aerodynamic characteristics分类
航空航天引用本文复制引用
厉聪聪,史勇杰,徐国华,马太行..基于前缘下垂的提升旋翼悬停气动特性研究[J].南京航空航天大学学报（英文版）,2021,38(z1):10-16,7.基金项目
This work was supported by the Na?tional Natural Science Foundation of China(No.11972190)and the Aeronautical Science Foundation of China(No.20185752). （No.11972190）
