摘要
近几年出现了许多构形新颖的垂直起降无人飞行器 ,都以涵道风扇作为升力系统。为了研究涵道风扇系统的气动特性 ,尤其是在复杂流场中涵道本身的升阻特性 ,在 3 .4m× 2 .4m开口风洞中对涵道风扇进行了吹风试验。试验模型由直径 1 .5 0 m的可变距风扇系统和外径 1 .8m的圆筒状涵道组成。试验状态变量包括涵道高度、吹风速度、涵道前倾角和风扇桨距。试验结果表明 :涵道在前飞状态比悬停状态产生更大的升力 ,但这一优势却被涵道的较大阻力所排斥 ,因而涵道风扇如果用作升力系统 ,仅适用于强调悬停和低速飞行的飞行器。
Some unmanned aerial vehicles can vertically take off and land with the ducted fan system, but there is no valid method to analyze the aerodynamic characteristics of a ducted fan system currently. An experimental research is completed in a 3 4 m×2 4 m wind tunnel, the purpose is to determine the aerodynamic characteristics of a ducted fan system, especially the lift and drag of the duct in the complex airflow. The test model is an annular duct with 1 8 m in diameter, and a 8-bladed fan with 1 50 m in diameter. Test variations include duct length, wind speed, duct angle of attack, and pitch angle of fan blades. Duct lift and drag data are measured under axial and forward flight conditions. Experimental results show that the duct can produce more lift under forward flight conditions than under axial conditions, but the drag of duct is too huge under forward flight conditions. As a kind of lift system, a ducted fan is only suitable to those aircrafts mainly operated at hovering and low speed flying.
出处
《南京航空航天大学学报》
EI
CAS
CSCD
北大核心
2004年第2期164-168,共5页
Journal of Nanjing University of Aeronautics & Astronautics
