Performance improvement of variable speed rotors by Gurney flaps

Han, D., Dong, C. and Barakos, G. N. (2018) Performance improvement of variable speed rotors by Gurney flaps. Aerospace Science and Technology, 81, pp. 118-127. (doi: 10.1016/j.ast.2018.07.044)

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Gurney flaps are used for improving the performance of variable speed rotors. An analytical model able to predict helicopter rotor power is first presented, and the flight data of the UH-60A helicopter is used for validation. The predictions of the rotor power are in good agreement with the flight test data, justifying the use of this tool in analyzing helicopter performance. A fixed Gurney flap can enhance the performance of variable speed rotors and expand the corresponding flight envelope, especially near stall and high speed flight. A retractable Gurney flap at 1/rev yields more power savings than a fixed Gurney flap or a retractable one with a higher harmonic prescribed motion. At a speed of 200 km/h, the retractable Gurney flap, actuated at 1/rev, can obtain 3.22% more power reduction at a rotor speed of 85% nominal rotor speed, and this value is 8.37% at a speed of 220 km/h. The height corresponding to the minimum power increases slowly in low to medium speed flight, and increases dramatically in high speed flight. With increasing take-off weight (i.e. rotor thrust), the retractable Gurney flap at 1/rev can obtain more rotor power savings.

Item Type:Articles
Additional Information:This work is supported from the National Natural Science Foundation of China (11472129), the Aeronautical Science Foundation of China (20165752048), and Science and Technology on Rotorcraft Aeromechanics Laboratory Foundation (6142220050416220002).
Glasgow Author(s) Enlighten ID:Barakos, Professor George
Authors: Han, D., Dong, C., and Barakos, G. N.
College/School:College of Science and Engineering > School of Engineering > Autonomous Systems and Connectivity
Journal Name:Aerospace Science and Technology
ISSN (Online):1626-3219
Published Online:30 July 2018
Copyright Holders:Copyright © 2018 Elsevier Masson SAS
First Published:First published in Aerospace Science and Technology 81: 118-127
Publisher Policy:Reproduced in accordance with the publisher copyright policy

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