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A comparative assessment of vibration control capabilities of a L-shaped Gurney flap

Published online by Cambridge University Press:  03 November 2016

V. Motta  and
G. Quaranta
V. Motta
Affiliation:
Dipartimento di Scienze e Tecnologie Aerospaziali, Politecnico di Milano, 20156 Milano, Italy
G. Quaranta*
Affiliation:
Dipartimento di Scienze e Tecnologie Aerospaziali, Politecnico di Milano, 20156 Milano, Italy
*
giuseppe.quaranta@polimi.it
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Abstract

This work presents the capabilities of a novel L-shaped trailing-edge Gurney flap as a device for vibration reduction. The primary effect of this L-tab is represented by a modification of the reference aerofoil mean line shape through by two counter-rotating vortical structures created at the trailing edge. The comparison of the aerodynamic loads generated by the novel L-tab Gurney flap and a classical trailing-edge flap allows to estimate the ranges of reduced frequency where the L-tab is expected to perform better than a trailing edge flap and vice versa. Linear aerostructural models for a typical section representative of a helicopter blade equipped with a partial-span L-tab or a trailing-edge flap are built, and a higher harmonic control algorithm is applied. Performance are compared between the two devices to reduce separately the N/rev harmonics of the blade root rotating frame vertical force, flapping and feathering moments. The attainment of similar results with classical trailing-edge device is a further confirmation of the potential feasibility of this novel L-tab as an effective alternative means for vibration reduction on rotor blades.

Keywords

aeroelasticityGurney flaphelicopter bladesrotorcraftvibration reduction
Type
Research Article
Information
The Aeronautical Journal , Volume 120 , Issue 1233 , November 2016 , pp. 1812 - 1831
Copyright
Copyright © Royal Aeronautical Society 2016 

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