Investigation of a NACA0012 Finite Wing Aerodynamics at Low Reynold’s Numbers and 0º to 90º Angle of Attack

Eftekhari, Shahrooz; Al-Obaidi, Abdulkareem Sh. Mahdi

doi:10.5028/jatm.v11.1023

Cited by 13 publications

(10 citation statements)

References 10 publications

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“…Typically, designers in the aeronautical industry seek to validate their simulation data through tests with a model of the designed aircraft [3]. However, in view of the impossibility of accessing the institution's Energy Laboratory to use the wind tunnel equipment, due to the current social isolation situation due to COVID-19, it was used as an alternative to validate the results of the CFD analysis the following two steps: 1) validation of the boundary conditions by comparison of the aerodynamic coefficients of non-deflected elevator with the work of [5]; 2) comparing the hinge moment results with the calculated when applied the correlations and data from [6].…”

Section: Results Validationmentioning

confidence: 99%

“…For the first step, the values of the lift and drag coefficients were compared, first for simulation results using the NACA 0012 profile without the elevator, against another CFD and experimental NACA 0012 data, allowing to evaluate the mesh quality and boundary conditions. The results were compared with the study by [5], which used the same turbulent model and similar Reynolds numbers applied in this analysis. Then, the same coefficients were extracted for the tail with the non-deflected elevator, as shown in the figure 4 above.…”

Section: Results Validationmentioning

confidence: 99%

“…For the results, a comparison between the simulation with the airfoil NACA 0012 and the results obtained through [5] in the graphics of lift and drag coefficient by alpha was made and the results have shown to be near.…”

Section: Resultsmentioning

confidence: 99%

See 2 more Smart Citations

Analysis of Elevator Hinge Moment in an Unmannedaerial Vehicle Designed for Sae Aerodesign Competitionusing CFD Simulation

Santos¹,

Oliveira²,

Oliveira³

et al. 2020

Blucher Engineering Proceedings

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This study had the general objective to analyze the resulting values of hinge moment in the elevator for the PM-03 project, of an unmanned aerial vehicle, dedicated for participation in the SAE Aero Design 2020 Competition. From 2D CAD modeling of surfaces using Solidworks, the hinge moment was analyzed in Ansys Fluent after generating an appropriate mesh and adjusting the initial flow settings. The validation of the CFD analysis was performed by comparing experimental results from another study and using USAF Datcom data and correlations. The results obtained by CFD and USAF DATCOM diverge, however, those allows to correctly estimate the order of magnitude of the hinge moment, allowing an optimized selection of the servo motor for the project.

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Section: Results Validationmentioning

confidence: 99%

Section: Results Validationmentioning

confidence: 99%

See 1 more Smart Citation

Analysis of Elevator Hinge Moment in an Unmannedaerial Vehicle Designed for Sae Aerodesign Competitionusing CFD Simulation

Santos¹,

Oliveira²,

Oliveira³

et al. 2020

Blucher Engineering Proceedings

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show abstract

“…Also the study used the C-Type grid topology to generate a ne mesh around the wing. Eftekhari and Al-obaidi in [10] added that the C-Type grid topology is an e cient meshing method for wing geometry requiring ne mesh for accurate results. The study indicates the drag coe cient increases as the AoA is increases, resulting in a change in the ow eld from laminar to turbulent, with ow separation in between.…”

Section: Review Of Related Literaturementioning

confidence: 99%

Numerical Investigation of Aerodynamic Characteristics of Wing of Ichoku-18 Unmanned Aerial Vehicle

Isah¹,

Lawal²,

Yahuza³

et al. 2022

Preprint

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An Unmanned Aerial Vehicle (UAV) whose wing consist of a combination of two different airfoils presents opportunity for improve aerodynamic performance; and research in this area has potential for significant innovation. This study employed a Computational Fluid Dynamic (CFD) technique to predict drag and lift coefficients and aerodynamic efficiency of the wing of Ichoku-18 (IU-18) UAV. The wing of the IU-18 UAV consists of two different aerofoil sections, NACA2415 at the root and SD7032 at the tip. The study investigates the aerodynamic characteristics of the wing at different Angle of Attack (AoA), AoA = 0°,4°, 8°, 12°, 16°, 20° and 24°. Using a standard and realizable k-ε turbulence models, the minimum and maximum drag coefficients and aerodynamic efficiencies were obtained at AoA = 0° and AoA = 24°. Both turbulence models predicted the critical angle of attack occurs at AoA = 16°. The results obtained were in agreement with analytical design data of the UAV and findings from the literature. While the standard k-ε turbulence model overpredicted the drag coefficients of the wing of IU-18 UAV, the values predicted by the realizable k-ε turbulence model were in closer agreement with the experimental data. Also, the lift coefficients predicted by the realizable k-ε turbulence model were more realistic and in closer agreement with that obtained analytically. Similarly, while the realizable k-ε turbulence models prediction of the CLmax is in closer agreement with the analytical data, the standard k-ε model underpredicted the variation of aerodynamic efficiency with AoA.

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“…Airplanes are a type of transportation that can lift heavy loads in the air. This happens because of the lift that can be generated by the aircraft's wings [1,2]. Efforts to research and develop airfoils or aircraft wings have been started since the 19th century.…”

Section: Introductionmentioning

confidence: 99%

Effect of Angle of Attack on Airfoil NACA 0012 Performance

Akbar¹

2020

r.e.m

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Airfoil is an aerodynamic form intended to produce a lift force with the smallest drag force. When an airfoil is passed through a fluid flow that causes interaction between the air flow and the surface, variations in velocity and pressure will occur along the top and bottom surfaces of the airfoil, as well as the front and back of the airfoil. The difference in pressure between the upper and lower surface of the airfoil is what causes the resultant force in the direction perpendicular to the direction of fluid flow, this force is called the lift force (lift). In this experiment NACA 0012 airfoil experiments have been carried out using simple wind tunnel. Experiments were conducted with the aim to determine the effect of the angle of attack on the performance of the NACA 0012 airfoil which then analyzed the lift force of the NACA 0012 airfoil. The variation of the angle of attack used was 0 °, 3 °, 6 °, 9 °, 12 °, and 15 ° and used wind speed of 21.5 m / s. The greatest lift force is obtained at an angle of attack of 9 ° with a value of 0.981 while the largest lifting coefficient with a value of 0.106. The greater the angle of attack the greater the airfoil lift force, but for symmetrical airfoil stall at an angle that is too large

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Investigation of a NACA0012 Finite Wing Aerodynamics at Low Reynold’s Numbers and 0º to 90º Angle of Attack

Cited by 13 publications

References 10 publications

Analysis of Elevator Hinge Moment in an Unmannedaerial Vehicle Designed for Sae Aerodesign Competitionusing CFD Simulation

Analysis of Elevator Hinge Moment in an Unmannedaerial Vehicle Designed for Sae Aerodesign Competitionusing CFD Simulation

Numerical Investigation of Aerodynamic Characteristics of Wing of Ichoku-18 Unmanned Aerial Vehicle

Effect of Angle of Attack on Airfoil NACA 0012 Performance

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