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Aerospace 2016, 3(4), 35; doi:10.3390/aerospace3040035

Numerical Investigation of Effect of Parameters on Hovering Efficiency of an Annular Lift Fan Aircraft

UAV Research Institute, Northwestern Polytechnical University, 127 West Youyi Road, Xi’an 710072, China
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Author to whom correspondence should be addressed.
Academic Editor: Mohammad Sadraey
Received: 14 August 2016 / Revised: 8 October 2016 / Accepted: 10 October 2016 / Published: 19 October 2016
(This article belongs to the Special Issue Aircraft Design)
View Full-Text   |   Download PDF [10538 KB, uploaded 19 October 2016]   |  

Abstract

The effects of various parameters on the hovering performance of an annular lift fan aircraft are investigated by using numerical scheme. The pitch angle, thickness, aspect ratio (chord length), number of blades, and radius of duct inlet lip are explored to optimize the figure of merit. The annular lift fan is also compared with a conventional circular lift fan of the same features with the same disc loading and similar geometry. The simulation results show that the pitch angle of 27°, the thickness of 4% chord length, the aspect ratio of 3.5~4.0, 32 blades, and the radius of inlet lip of 4.7% generate the maximum figure of merit of 0.733. The optimized configuration can be used for further studies of the annular lift fan aircraft. View Full-Text
Keywords: annular duct; ducted fan; lift fan; hovering efficiency; optimization; aircraft annular duct; ducted fan; lift fan; hovering efficiency; optimization; aircraft
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This is an open access article distributed under the Creative Commons Attribution License which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited. (CC BY 4.0).

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Jiang, Y.; Zhang, B. Numerical Investigation of Effect of Parameters on Hovering Efficiency of an Annular Lift Fan Aircraft. Aerospace 2016, 3, 35.

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