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    AERODYNAMIC ANALYSIS OF A SUBSONIC AIRCRAFT WING USING COMPUTATIONAL FLUID MODELLING
    (EUROSIS-ETI, 2024) Jweeg, M.J.; Bakirci, M.; Ismael, I.J.
    Aircraft designers are mainly interested in finding the level of pressure, stresses and deformations of the parts of the aircraft, especially the wing, as in many aviation accidents, the failure of the wing was the main cause of disasters due to the aerodynamic loading. In this work, the numerical study was achieved to obtain the aerodynamic loading, span wise and chord wise. In this respect, the volume method was used to predict the pressure distribution of the wing in the subsonic potential flow. The singularity strength which satisfies the boundary condition of the tangential flow at the control point for a given Mach number and the angle of attack was employed in the package in which the design was achieved using the 3D geometry model by using the Software SOLIDWORKS 2020 and the second step was processing the governing differential equations for airflow over a wing by ANSYS FLUENT 2022 R1 version solver by utilizing a Finite Element Method. Finally, the results were compared with other research which have shown to be in good agreement. © 2024, EUROSIS-ETI. All rights reserved.
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    An Optimum Design of a Subsonic Aircraft Wing due to the Aerodynamic Loading
    (Hindawi Limited, 2024) Ismeal, I.J.; Bakirci, M.; Jweeg, M.J.
    Aircraft designers are mainly interested in finding the level of pressure, stresses, and deformations of the parts of the aircraft wing. In many aviation accidents, the failure of the wing is the main cause of disasters, as it is considered the main surface that generates the necessary lift for the aircraft in addition to its other functions in controlling the transverse stability. In this work, a numerical study was performed to obtain the optimum wing structural design parameters for high strength and minimum weight for the L-39 A/C wing. The wing was modeled as a honeycomb with different thicknesses using the software SOLIDWORKS 2020. The pressure distribution was predicted using the FLUENT 2022 R1 package. Having obtained the aerodynamic pressure, the deformations and stresses were obtained using the ANSYS program. The results were compared with other researchers using other models, such as using ribs and stringers in the interior structure of the wing. The current results were found to be reliable and acceptable from the design point of view of the high stiffness-to-weight ratio. © 2024 Ibtisam J. Ismeal et al.