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Experimental investigation of a helicopter rotor with Gurney flaps

Published online by Cambridge University Press:  24 January 2017

G. Gibertini ,
A. Zanotti ,
G. Droandi ,
F. Auteri  and
G. Crosta
G. Gibertini*
Affiliation:
Dipartimento di Scienze e Tecnologie Aerospaziali, Politecnico di Milano, Milano, Italy
A. Zanotti
Affiliation:
Dipartimento di Scienze e Tecnologie Aerospaziali, Politecnico di Milano, Milano, Italy
G. Droandi
Affiliation:
Dipartimento di Scienze e Tecnologie Aerospaziali, Politecnico di Milano, Milano, Italy
F. Auteri
Affiliation:
Dipartimento di Scienze e Tecnologie Aerospaziali, Politecnico di Milano, Milano, Italy
G. Crosta
Affiliation:
Leonardo Helicopters, HSD Department, via G.Agusta 520, Cascina Costa di Samarate (VA), Italy
*
[email protected]
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Abstract

The present work describes an experimental activity carried out to investigate the performance of Gurney flaps on a helicopter rotor model in hovering. The four blades of the articulated rotor model were equipped with Gurney flaps positioned at 95% of the aerofoil chord, spanning 14% of the rotor radius. The global aerodynamic loads and torque were measured for three Gurney flap configurations characterised by different heights. The global measurements showed an apparent benefit produced by Gurney flaps in terms of rotor performance with respect to the clean blade configuration. Particle image velocimetry surveys were also performed on the blade section at 65% of the rotor radius with and without the Gurney flaps. The local velocity data was used to complete the characterisation of the blade aerodynamic performance through the evaluation of the sectional aerodynamic loads using the the control volume approach.

Keywords

helicoptergurney flaprotorparticle image velocimetry
Type
Research Article
Information
The Aeronautical Journal , Volume 121 , Issue 1236 , February 2017 , pp. 191 - 212
Copyright
Copyright © Royal Aeronautical Society 2017 

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