Researchon Aerodynamic Design of High Altitude High Thrust Ducted Fan
On the basis of the thrust ducted fan of aircraft,NASA ducted fan model and experimental data are applied to conduct numerical calculation and verification.By self-compiled code,the overall performance parameters of the ducted fan in hovering state are solved in line with the design requirements.The fan blades are designed by the leaf element theory.According to the numerical results of the initial model,the key components of the ducted fan are optimized,and a new type of ducted profile section is abtained.The results show that the increase of the radius of the guide circle at the culvert lip will reduce the separation at the lip,thus increasing the flow at the inlet and outlet of the fan.The outlet axial speed of the ducted fan is increased by reducing the outlet installation angle of the blade from 60％to 100％.The optimization of the two components jointly improves the lift of the ducted fan and meets the design index requirements.
万方数据
维普
