Rotor Computations with Active Gurney Flaps

Woodgate, M.; Pastrikakis, Vasileios; Barakos, George N.

doi:10.1007/978-3-319-27386-0_9

Cited by 9 publications

(12 citation statements)

References 22 publications

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“…For the purposes of this study the gurney flap on the W3-Sokol MRB is modelled by flagging any cell face within the computational mesh occupied by the flap with a solid, no-slip boundary condition. This method is implemented in the HMB solver and has been proved to be simple and effective by Woodgate and Barakos (2012). In this case the gurney is assumed to be thin, and is modelled along a block boundary.…”

Section: Modelling Gurney Flapsmentioning

confidence: 99%

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Computational aeroelastic analysis of a hovering W3 Sokol blade with gurney flap

Pastrikakis

Steijl

Barakos

et al. 2015

Journal of Fluids and Structures

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This paper demonstrates the potential effect of a gurney flap on the performance of the W3-Sokol rotor blade in hover. A rigid blade was first considered and the calculations were conducted at several thrust settings. The gurney flap was extended from 46%R to 66%R and it was located at the trailing edge of the main rotor blade. Four different sizes of gurney flaps were studied, 2%, 1%, 0.5% and 0.3% of the chord. The biggest flap proved to be the most effective. A second study considered elastic blades with and without the gurney flap. The results were trimmed at the same thrust values as the rigid blade and indicate an increase of aerodynamic performance when the gurney flap is used, especially for high thrust cases. Keywords

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Section: Modelling Gurney Flapsmentioning

confidence: 99%

“…The advantage of this method is that no additional effort is needed in terms of mesh generation. The results of the method were presented by Woodgate and Barakos (2012).…”

Section: Modelling Gurney Flapsmentioning

confidence: 99%

Computational aeroelastic analysis of a hovering W3 Sokol blade with gurney flap

Pastrikakis

Steijl

Barakos

et al. 2015

Journal of Fluids and Structures

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“…Computational Fluid Dynamic (CFD) techniques are also frequently used to study the advantages and limitations of different flow control devices [24]. Recently, Woodgate et al [25] used an in-house CFD solver to evaluate the implementation of GFs on wings and rotors. Different methods of modeling a GF were discussed and 2D cases were simulated to compare thick and infinitely thin GFs.…”

Section: Introductionmentioning

confidence: 99%

Parametric Study of a Gurney Flap Implementation in a DU91W(2)250 Airfoil

et al. 2019

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The growth in size and weight of wind turbines over the last years has led to the development of flow control devices, such as Gurney flaps (GFs). In the current work, a parametric study is presented to find the optimal GF length to improve the airfoil aerodynamic performance. Therefore, the influence of GF lengths from 0.25% to 3% of the airfoil chord c on a widely used DU91W(2)250 airfoil has been investigated by means of RANS based numerical simulations at Re = 2 × 106. The numerical results showed that, for positive angles of attack, highest values of the lift-to-drag ratio CL/CD are obtained with GF lengths between 0.25% c and 0.75% c. Particularly, an increase of 21.57 in CL/CD ratio has been obtained with a GF length of 0.5% c at 2° of angle of attack AoA. The influence of GFs decreased at AoAs larger than 5°, where only a GF length of 0.25% c provides a slight improvement in terms of CL/CD ratio enhancement. Additionally, an ANN has been developed to predict the aerodynamic efficiency of the airfoil in terms of CL/CD ratio. This tool allows to obtain an accurate prediction model of the aerodynamic behavior of the airfoil with GFs.

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“…This allows a flap of infinite thickness, normal to the trailing edge, to be simulated. The process of localising the flap and flagging cells as solid is described by Woodgade and Barakos (34) . The mesh used for the forward flight calculations consists of 27 million nodes.…”

Section: Mrb Geometrymentioning

confidence: 99%

Effect of active Gurney flaps on overall helicopter flight envelope

2016

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This paper presents a study of the W3-Sokol main rotor equipped with Gurney flaps.The effect of the a active Gurney is tested at low and high forward flight speeds to draw conclusions about the potential enhancement of the rotorcraft performance for the whole flight envelope. The effect of the flap on the trimming and handling of a full helicopter is also investigated. Fluid and structure dynamics were coupled in all cases, and the rotor was trimmed at different thrust coefficients. The Gurney proved to be efficient at medium to high advance ratios, where the power requirements of the rotor were decreased by up to 3.3%. However, the 1/rev actuation of the flap might be an issue for the trimming and handling of the helicopter. The current study builds on the idea that any active mechanism operating on a rotor could alter the dynamics and the handling of the helicopter. A closed loop actuation of the Gurney flap was put forward based on a pressure divergence criterion, and it led to further enhancement of the aerodynamic performance. Next, a generic light utility helicopter was built using 2D aerodynamics of the main aerofoil section of the W3 Sokol blade along with a robust controller, and the response of the rotorcraft to control inputs was tested. This analysis proved that the 1/Rev actuation of the Gurney did not alter the handling qualities of the helicopter, and as a result it can be implemented as a flow control mechanism for aerodynamic enhancement and retreating blade stall alleviation. * Ph.D, email: vpastrikakis@gmail.com † Senior lecturer, email: Rene.Steijl@glasgow.ac.uk ‡ Professor, email: George.Barakos@glasgow.ac.uk, Corresponding author. of 42The Aeronautical Journal The Aeronautical Journal

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Rotor Computations with Active Gurney Flaps

Cited by 9 publications

References 22 publications

Computational aeroelastic analysis of a hovering W3 Sokol blade with gurney flap

Computational aeroelastic analysis of a hovering W3 Sokol blade with gurney flap

Parametric Study of a Gurney Flap Implementation in a DU91W(2)250 Airfoil

Effect of active Gurney flaps on overall helicopter flight envelope

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