Experimental study of helicopter fuselage drag

Stepanov, R., Zherekov, V., Pakhov, V., Mikhailov, S., Garipov, A., Yakubov, W. and Barakos, G. N. (2016) Experimental study of helicopter fuselage drag. Journal of Aircraft, 53(5), pp. 1343-1360. (doi: 10.2514/1.C033819)

116394.pdf - Accepted Version



Experimental data are presented for the parasite drag of various helicopter fuselage components, such as skids, external fuel tanks, and tailplane. The experiments were conducted at the Kazan National Research Technical University (Kazan Aviation Institute) T-1K wind tunnel, investigating four versions of a fuselage similar to the Ansat helicopter. It was found that, for the range of pitch angles −10≤α≤10  deg−10≤α≤10  deg, the skids added 80% to the drag of the bare fuselage, whereas the tailplane increased the drag by 20%. At the same conditions, external fuel tanks were found to add 48% to the clean fuselage drag. A simple rotor hub with a tail support added 74% to the bare fuselage in the range of pitch angles −8≤α≤6  deg−8≤α≤6  deg. Streamlining the rear fuselage was found to reduce the drag by 16% over the range of pitch angles −10≤α≤10  deg−10≤α≤10  deg. Apart from the parasite drag, ideas for drag reduction are also discussed.

Item Type:Articles
Additional Information:This work was supported by the grant “State Tasks in the Field of Scientific Activity” (number 9.1694.2014/K) of the Ministry of Education and Science of the Russian Federation.
Glasgow Author(s) Enlighten ID:Barakos, Professor George
Authors: Stepanov, R., Zherekov, V., Pakhov, V., Mikhailov, S., Garipov, A., Yakubov, W., and Barakos, G. N.
College/School:College of Science and Engineering > School of Engineering > Autonomous Systems and Connectivity
Journal Name:Journal of Aircraft
Publisher:American Institute of Aeronautics and Astronautics
ISSN (Online):1533-3868
Published Online:26 July 2016
Copyright Holders:Copyright © 2015 The Authors
First Published:First published in Journal of Aircraft 53(5): 1343-1360
Publisher Policy:Reproduced in accordance with the publisher copyright policy

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