Numerical Investigation of Rib Structure Effects On Performance of Wind Turbines

Tanürün, Himmet Erdi; Akin, Ahmet Giray; Acır, Adem

doi:10.2339/politeknik.845804

Cited by 6 publications

(8 citation statements)

References 22 publications

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“…Figure 2 shows created models. The dimensions of the rib structure were taken from Tanürün et al's study [7]. A plain flap was created with an angle of 25°.…”

Section: 2modelling the Airfoilsmentioning

confidence: 99%

“…Symmetry boundary condition was used for both the upper and bottom sides. The distance between the upper and the bottom side is equal to 20 c. While selecting these distances, existing studies from the literature were considered [7,14].…”

Section: Figure 3 Computational Domainmentioning

confidence: 99%

“…As a result of their study, they found that at higher α values, triangular rib structure enhances the aerodynamic performance. When α > 15°, the lift-to-drag ratio (𝐶 𝐿 /𝐶 𝐷 ) was increased by utilizing the rib structure on the airfoil [7]. Venkatesan et al investigated the effects of square, rectangle and triangle dimples on the NACA 2412 airfoil's aerodynamic behavior.…”

Section: Introductionmentioning

confidence: 99%

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Investigation of a Rib Structure Effect on the Aerodynamic Performance of a Plain Flapped Symmetrical Airfoil

Kaya

2023

Journal of Polytechnic

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In this paper, two-dimensional computational fluid dynamics analyses were conducted to examine the rib effect on the performance of the NACA 0018 plain flapped airfoil. A mesh independence study was carried out and the Spalart-Allmaras turbulence model was selected for validation. Four various airfoil models were designed: M1 (airfoil without plain flap and rib structure), M2 (airfoil with rib structure), M3 (airfoil with a plain flap) and M4 (airfoil with a rib structure and plain flap). The performance of designed airfoils was calculated in terms of lift-to-drag (C_L/C_D) ratio. As a result, the plain flap significantly increased the lift coefficient (C_L) and drag coefficient (C_D). While the rib structure enhanced the aerodynamic performance of the non-flapped airfoil when the attack angle was greater than 12°, it increased the performance of the plain flapped airfoil at almost all attack angles. Furthermore, it was seen that the rib structure decreased C_D values of plain flapped airfoil at all attack angles and increased C_L values of plain flapped airfoil when the attack angle was greater than 2°.

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“…Figure 2 shows created models. The dimensions of the rib structure were taken from Tanürün et al's study [7]. A plain flap was created with an angle of 25°.…”

Section: 2modelling the Airfoilsmentioning

confidence: 99%

Section: Figure 3 Computational Domainmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Investigation of a Rib Structure Effect on the Aerodynamic Performance of a Plain Flapped Symmetrical Airfoil

Kaya

2023

Journal of Polytechnic

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“…The aerodynamic properties of the humpback whale were numerically examined in the modified NACA 0015 and it was determined that the modified M1 airfoil provided an improvement of 3.81% [19]. When the effect of rib structure on NACA 2412 was examined, it was reported that the stall angle was delayed thanks to the rib structure [20]. In current study, numerical analyses were carried out to estimate the lift and drag coefficients of Eppler 423 and NACA6409 airfoils, which give high lift to low Reynolds numbers, using ANSYS Fluent 19.0, a commercial computational fluid dynamics software.…”

Section: Introductionmentioning

confidence: 99%

Numerical Analysis of NACA 6409 and Eppler 423 Airfoils

Durmuş¹,

Ulutaş²

2023

Politeknik Dergisi

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 Current paper focuses on RANS based turbulence analysis of NACA 6409 and Eppler 423.  θ-Reθ SST was the RANS model that gave the most consistent results with the experimental data.  CFD Simulation results of pressure and velocity fields at different angles of attack are clearly presented.  CFD results with experimental data and XFoil are evaluated in terms of best glide ratio-(Cl/Cd)max and minimum sink-(Cl 1.5 /Cd)max criteria.

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“…An airfoil with the lowest drag and highest lift coefficients should be used during the flow [1][2][3][4]. In the literature, there are studies examining many airfoil behaviors [5][6][7][8][9][10][11][12][13][14][15][16][17][18][19][20]. In most of these studies, many angles of attack were discussed.…”

Section: Introductionmentioning

confidence: 99%

NACA0009 ve NACA4415 Kanat Profillerinin Sayısal ve İstatistiksel Aerodinamik Performans Analizi

Evran

YILDIR

2023

Journal of Polytechnic

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In this numerical and statistical study, lift and drag coefficient performances of NACA-0009 and NACA-4415 airfoils were evaluated in accordance with various attack angle at constant velocity of wind. Lift and drag coefficients of airfoils was numerically determined by computational fluid dynamics code ANSYS FLUENT. Analysis design of numerical calculations was implemented using L16 orthogonal array based on Taguchi method. Angles of attack and airfoil types were considered as control factors. The optimum level and effect of each control factor on responses was statistically implemented using analyses of Signal-to-Noise ratio and variance. As a result of this study, maximum lift and minimum drag coefficient were achieved by using NACA4415 airfoil compared to NACA0009 airfoil. The increase of the angle of attack leads to the increase on the lift and drag coefficients for both airfoils.

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Numerical Investigation of Rib Structure Effects On Performance of Wind Turbines

Abstract: Rüzgâr türbinlerinde kiriş yapısının performansa etkisinin sayısal olarak incelenmesi Numerical investigation of rib structure effects on performance of wind turbines

Cited by 6 publications

References 22 publications

Investigation of a Rib Structure Effect on the Aerodynamic Performance of a Plain Flapped Symmetrical Airfoil

Investigation of a Rib Structure Effect on the Aerodynamic Performance of a Plain Flapped Symmetrical Airfoil

Numerical Analysis of NACA 6409 and Eppler 423 Airfoils

NACA0009 ve NACA4415 Kanat Profillerinin Sayısal ve İstatistiksel Aerodinamik Performans Analizi

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