Numerical Simulation on the Flow Control by Mounting Indented Gurney Flaps for a Wind Turbine

Zhao, Wan Li; Zheng, Xiao Lei

doi:10.4028/www.scientific.net/amr.512-515.623

Cited by 5 publications

(4 citation statements)

References 10 publications

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“…Accordingly, the range of height that could improve aerodynamic performance is between 1 and 3.2% of airfoil chord (Jang et al , 1998; Tang and Dowell, 2006; Xie et al , 2016). As, the gurney flap height is so important in aerodynamic performance, the airfoil thickness is important too, especially in wind turbines (Zhao and Zheng, 2012).…”

Section: Effects Of Gurney Flap Heightmentioning

confidence: 99%

Dynamic stall of an airfoil with different mounting angle of gurney flap

Masdari

Mousavi

Tahani

2020

AEAT

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Purpose One of the best methods to improve wind turbine aerodynamic performance is modification of the blade’s airfoil. The purpose of this paper is to investigate the effects of gurney flap geometry and its oscillation parameters on the pitching NACA0012 airfoil. Design/methodology/approach This numerical solution has been carried out for different cases of gurney flap mounting angles, heights, reduced frequencies and oscillation amplitudes, then the results were compared to each other. The finite volume method was used for the discretization of the governing equations, and the PISO algorithm was used to solve the equations. Also, the “SST” was adopted as the turbulence model in the simulation. Findings In this paper, the different parameters of gurney flap were investigated. The results showed that the best range of gurney flap height are between 1 and 3.2% of chord and the best ratio of lifting to drag coefficient is achieved in gurney flap with an angle of 90° relative to the chord direction. The dynamic stall angle of the airfoil with gurney flap decreases were compared to without gurney flap. Earlier LEV formation can be one of the main reasons for decreasing the dynamic stall angle of the airfoil with gurney flap. Increasing the reduced frequency and oscillation amplitude causes rising of maximum lift coefficient and consequently lift curve slope. Moreover, gurney flap with mounting angle has a lower hinge moment than the gurney flap without mounting angle but with the same vertical axis length. So, there is more complexity in structural design concerning the gurney flap without mounting angle. Practical implications Improving aerodynamic efficiency of airfoils is vital for obtaining more output power in VAWTs. Gurney flaps are one of the best mechanisms to increase the aerodynamic performance of the airfoil and increases the efficiency of VAWTs. Originality/value Investigating the hinge moment on the connection point of the airfoil, gurney flap and try to compare the gurney flap with and without angle.

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Section: Effects Of Gurney Flap Heightmentioning

confidence: 99%

Dynamic stall of an airfoil with different mounting angle of gurney flap

Masdari

Mousavi

Tahani

2020

AEAT

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“…The flaps include Gurney flap, Discreting trailing edge flap, deformable trailing edge flap and micro sliding flap (MICROTAB). Studies show that Gurney flap can improve the pressure distribution of the airfoil and increase the lift coefficient and lift-to-drag ratio of it [1][2][3]. Troldborg has calculated Steady aerodynamics of the fixed trailing edge flap using CFD method.…”

Section: Introductionmentioning

confidence: 99%

“…The lift coefficient and lift-to-drag ratio of the airfoil can be increased by the method listed above. But Strength of the connecting structure of Gurney flap and the airfoil will cause some new problems [3]. MICROTAB can be easily controlled, but it is very expensive.…”

Section: Introductionmentioning

confidence: 99%

Influence of Flap Deflection Angle on Wind Turbine Airfoil with Trailing Edge Flaps

Jia

Han

et al. 2014

AMR

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To improve the ability of capturing the wind energy of wind turbine and shorten the design period is of great importance to designing wind turbine blade. The article established S809 airfoil model with trailing edge flaps, The gap of the frontal subject and trailing edge flap adopt uniform gap structure, this structure will reduce the influence of the gap on aerodynamic characteristics.Using the k-ω Two equation turbulence model , the article calculated aerodynamic performance of S809 with 10% chord length trailing edge flaps under different deflecting angles. Results show that gap between the main body and trailing edge flap has little effect on airfoil aerodynamic performance, however, the deflection Angle of Trailing edge flap have great affect on airfoil aerodynamic performance, when deflection Angle of trailing edge flap is 14 ° degrees ,the lift-to-drag ratio is the largest.

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“…Flap is also a kind of flow control method. Zhao and Zheng [10] simulated the wind turbine with Gurney flap. Cole et al [11] tested the various airfoils with Gurney flaps in the wind tunnel.…”

Section: Introductionmentioning

confidence: 99%

Numerical and Experimental Investigation on the Flow Separation Control of S809 Airfoil with Slot

Xie

Chen

et al. 2013

Mathematical Problems in Engineering

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A new flow control approach called split blade is applied on the S809 airfoil in the present study. S809 airfoil was investigated experimentally and numerically with different operating conditions including cascade without control, cascade with slots that generate jets with AOAs of 0 degrees, 10 degrees, 15 degrees and 20 degrees. Good agreement was obtained between the comparison of the experimental and numerical results. The results show that the separation area increases with increase of the AOA and the large separation area appears on the airfoil suction surface at AOA equal to 20 degrees. Numerical results show that the control method has little negative influence on the airfoil performance at small AOAs. Smaller vortices are filled with the large separated area which is divided by the jet generated by split when the AOA is 20 degrees. The analysis on the lift coefficient and drag coefficient shows that the flow is improved with the control. The lift coefficient and drag coefficient do not change in the comparison between the cases before and after control when AOA is 0 degrees and 10 degrees. However, the lift coefficient increases and drag coefficient decreases when AOA is 15 degrees and 20 degrees. Hindawi Publishing Corporation

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Numerical Simulation on the Flow Control by Mounting Indented Gurney Flaps for a Wind Turbine

Cited by 5 publications

References 10 publications

Dynamic stall of an airfoil with different mounting angle of gurney flap

Dynamic stall of an airfoil with different mounting angle of gurney flap

Influence of Flap Deflection Angle on Wind Turbine Airfoil with Trailing Edge Flaps

Numerical and Experimental Investigation on the Flow Separation Control of S809 Airfoil with Slot

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