An Optimum Design of a Subsonic Aircraft Wing due to the Aerodynamic Loading

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dc.contributor.authorIsmeal, I.J.
dc.contributor.authorBakirci, M.
dc.contributor.authorJweeg, M.J.
dc.date.accessioned2024-09-29T16:16:37Z
dc.date.available2024-09-29T16:16:37Z
dc.date.issued2024
dc.departmentKarabük Üniversitesien_US
dc.description.abstractAircraft 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.en_US
dc.identifier.doi10.1155/2024/8867496
dc.identifier.issn2356-6140
dc.identifier.pmid38268746en_US
dc.identifier.scopus2-s2.0-85183502875en_US
dc.identifier.scopusqualityQ2en_US
dc.identifier.urihttps://doi.org/10.1155/2024/8867496
dc.identifier.urihttps://hdl.handle.net/20.500.14619/9225
dc.identifier.volume2024en_US
dc.indekslendigikaynakScopusen_US
dc.indekslendigikaynakPubMeden_US
dc.language.isoenen_US
dc.publisherHindawi Limiteden_US
dc.relation.ispartofScientific World Journalen_US
dc.relation.publicationcategoryMakale - Uluslararası Hakemli Dergi - Kurum Öğretim Elemanıen_US
dc.rightsinfo:eu-repo/semantics/openAccessen_US
dc.subjectaluminumen_US
dc.subjectcarbonen_US
dc.subjectaircraften_US
dc.subjectarchitectureen_US
dc.subjectArticleen_US
dc.subjectdensityen_US
dc.subjectdesignen_US
dc.subjectdynamicsen_US
dc.subjectexperimenten_US
dc.subjectfinite element analysisen_US
dc.subjectquantitative studyen_US
dc.subjectstrengthen_US
dc.subjecttensile strengthen_US
dc.subjectthermal conductivityen_US
dc.subjectYoung modulusen_US
dc.subjectaircraft accidenten_US
dc.subjectarticleen_US
dc.subjectnonhumanen_US
dc.subjectpressureen_US
dc.subjectquantitative studyen_US
dc.subjectsoftwareen_US
dc.subjectthicknessen_US
dc.subjectwingen_US
dc.titleAn Optimum Design of a Subsonic Aircraft Wing due to the Aerodynamic Loadingen_US
dc.typeArticleen_US

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