Comparing the Effect of Different Turbulence Models on The CFD Predictions of NACA0018 Airfoil Aerodynamics

Khan, Sher Afghan; Bashir, Musavir; Baig, Maughal Ahmed Ali; Ali, Fharukh Ahmed Ghasi Mehaboob

doi:10.37934/cfdl.12.3.110

Cited by 16 publications

(8 citation statements)

References 17 publications

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“…To close the system (1) and to determine the coefficient of turbulent viscosity. The different turbulence models were discussed in a study by Khan et al, [18]. The Spalart-Allmaras model was used herein, which was well-proven at the analysis of problems of external flow around bodies and is described in detail in the study by Spalart and Allmaras [19].…”

Section: Methodology 21 Mathematical Statement Of the Problemmentioning

confidence: 99%

Numerical Study of Aerodynamic Characteristics of a Pointed Plate of Variable Elongation in Subsonic and Supersonic Gas Flow

Alekseyenko

Dreus

Dron

et al. 2022

ARFMTS

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This study shows a thick plate, pointed on both sides, of variable elongation under action of subsonic and supersonic air flows. The relevance of the work is driven by the development of new aircraft that change their geometry during the flight, in particular, aircraft that change the relative elongation during the flight. The aim of this work is to determine the aerodynamic fields around the pointed plate, taking into account its variable elongation, and to determine the effect of variable elongation on the drag coefficient of the plate. Numerical simulation was used as a research tool. Mathematical modeling is based on Reynolds-averaged Navier-Stokes equations. The original software was used for the analysis; the computational algorithm is based on the finite volume method. The mathematical model and algorithm of numerical computation of subsonic and supersonic air flow acting on a pointed plate are presented. A pattern of gas flow acting on the plate is obtained at zero angle of attack for Mach numbers from 0,6 to 4. The dependence of the plate drag coefficient on Mach number and relative elongation is obtained. It is established that for a thick pointed plate the drag coefficient significantly depends on the elongation for both sound and supersonic flow. As a result of numerical experiments, the anomalous behavior of the drag coefficient in the transonic area at large elongations was found. It is shown that the decrease in elongation leads to an increase in the drag coefficient of the plate, which affects the aerodynamic characteristics of the aircraft of variable elongation.

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Section: Methodology 21 Mathematical Statement Of the Problemmentioning

confidence: 99%

Numerical Study of Aerodynamic Characteristics of a Pointed Plate of Variable Elongation in Subsonic and Supersonic Gas Flow

Alekseyenko

Dreus

Dron

et al. 2022

ARFMTS

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“…A more promising approach is to include a transition model to more accurately simulate the complex boundary layers typical for airfoils and high-lift configurations. Khan et al [27] successfully used the k-k L -ω model to improve the predictive accuracy for a symmetrical airfoil. This was also tested for slat and airfoil configurations investigated in this paper, but resulted in a drastic over-prediction of the maximum lift (see Figure 6).…”

Section: Turbulence Modelmentioning

confidence: 99%

Investigation and Optimisation of High-Lift Airfoils for Airborne Wind Energy Systems at High Reynolds Numbers

Fischer

Church

Nayeri

et al. 2023

Wind

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The potential of airfoil optimisation for the specific requirements of airborne wind energy (AWE) systems is investigated. Experimental and numerical investigations were conducted at high Reynolds numbers for the S1223 airfoil and an optimised airfoil with thin slat. The optimised geometry was generated using the NSGA-II optimisation algorithm in conjunction with 2D-RANS simulations. The results showed that simultaneous optimisation of the slat and airfoil is the most promising approach. Furthermore, the choice of turbulence model was found to be crucial, requiring appropriate transition modeling to reproduce experimental data. The k-ω-SST-γ-Reθ model proved to be most suitable for the geometries investigated. Wind tunnel experiments were conducted with high aspect ratio model airfoils, using a novel structural design, relying mostly on 3D-printed airfoil segments. The optimised airfoil and slat geometry showed significantly improved maximum lift and a shift of the maximum power factor to higher angles of attack, indicating good potential for use in AWE systems, especially at higher Reynolds numbers. The combined numerical and experimental approach proved to be very successful and the overall process a promising starting point for future optimisation and investigation of airfoils for AWE systems.

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“…Eleni et al, [25] demonstrated that the kῳ-SST model is appropriate for NACA 0012 airfoil design and provides accurate analyses and vortex at all angles of attack. Furthermore, according to references [28,30,31], k SST simulated the boundary layers along the airfoil's wall, which is necessary for capturing accurate results through numerical computations. Based on these researches, the Kῳ-SST model is selected for all domains in the current work for both airfoils with and without inclined trailing edge.…”

Section: Numerical Simulationmentioning

confidence: 99%

Modified Trailing Edge Impact on the Aerodynamic Performance of Wind Turbine Airfoil

Jaafar

Abdelrahman

Mourad

et al. 2022

ARFMTS

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One of the most important factors affecting wind turbine performance is the airfoil. The impact of the NACA 0012 trailing edge design on airfoil performance is investigated numerically in this paper. Computational fluid dynamics calculations are used to design and simulate the airfoils. The thick trailing edge is inclined to various angles to achieve further improvement in the lift/drag ratio and lift coefficient. The results reveal that, when compared with baseline airfoil, all the designed airfoils demonstrated higher lift coefficients. The lift coefficient increases with the angle of the inclined trailing edge. The maximum lift coefficient improvement inclined airfoil is 74%. In addition, the lift/drag ratio increases with the increase of the inclined angle, and the maximum improvement ratio reaches 39.495% for the inclined airfoil with Ꝋ=15º. Any further increase in the inclined angle decreases the lift/drag ratio as a result of drag increase. This study contributes toward the design of efficient wind turbine airfoils.

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Comparing the Effect of Different Turbulence Models on The CFD Predictions of NACA0018 Airfoil Aerodynamics

Cited by 16 publications

References 17 publications

Numerical Study of Aerodynamic Characteristics of a Pointed Plate of Variable Elongation in Subsonic and Supersonic Gas Flow

Numerical Study of Aerodynamic Characteristics of a Pointed Plate of Variable Elongation in Subsonic and Supersonic Gas Flow

Investigation and Optimisation of High-Lift Airfoils for Airborne Wind Energy Systems at High Reynolds Numbers

Modified Trailing Edge Impact on the Aerodynamic Performance of Wind Turbine Airfoil

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