摘要
Abstract
At present,most of the research on installing Gurney flaps is focused on two-dimensional airfoils.The three-dimensional blade model is established to investigate the influence of different Gurney flap parameters on ro-tor aerodynamic performance.Firstly,a three-dimensional numerical method for rotor aerodynamic characteristics with Gurney flap is established,and verified with typical experimental data.Then,the effects of different lengths,heights,and radial positions of the Gurney flap on the aerodynamic performance of the rotor are analyzed.Finally,by analyzing the pressure distribution on the blade surface,the pressure coefficient at the Gurney flap location,and changes in streamlines after installing the Gurney flap on the blade,the lift augmentation mechanism of the rotor blade equipped with the Gurney flap is preliminarily explored.The results show that when the Gurney flap height is 2%c,the length is 0.2R,and the center position is 0.7R,the rotor thrust is increased by 14.15%.The double vor-tex structure formed behind the Gurney flap can create a suction effect on the upper surface of the airfoil,which can delay flow separation on the upper surface of the blade,thereby enhancing the rotor thrust.关键词
直升机/悬停/格尼襟翼/参数分析/气动特性/机理研究Key words
helicopter/hover/Gurney flap/parameter analysis/aerodynamic characteristics/mechanism study分类
航空航天
