摘要
对一种新型可倾转有翼微型涵道飞行器进行了风洞实验,以研究它的空气动力特性。在实验过程中采用全尺寸模型,分别进行关电机、单电机和双电机三种模式风洞实验。通过实测螺旋桨转速、风速、迎角和升降舵偏角对涵道飞行器气动力和力矩的影响,得到了一些涵道飞行器特有的气动特性,其结果可作为理论建模的依据。
Wind tunnel experiment is employed to study the aerodynamic characteristics of a novel micro tilt ducted fan MAV. Full-scale model is adopted in the wind tunnel experiment. The experiment focus on three modes： no motor, single motor and dual motors, respectively. The influences of design parameters on aerodynamic forces and moments are measured to get some typical aerodynamic characteristics. The tcst re- suits are useful for theoretical modeling.
出处
《空气动力学学报》
EI
CSCD
北大核心
2012年第6期777-781,共5页
Acta Aerodynamica Sinica
基金
国家自然科学基金(11002072)
关键词
涵道
飞行器
倾转
风洞实验
气动特性
duct
aircraft
tilt
wind tunnel experiment
aerodynamic characteristics
