A Computational Study on NACA 2412 Airfoil with a Leading-Edge Dimple

A Computational Study on NACA 2412 Airfoil with a Leading-Edge Dimple | Research Square window.SnipcartSettings = { analytics: { enabled: false } }; (function() { var accessVector = localStorage.getItem('access_vector') || ''; window.dataLayer = window.dataLayer || []; if (accessVector) { window.dataLayer.push({ user: { profile: { profileInfo: { snid: accessVector } } } }); } })(); (function(w,d,s,l,i){w[l]=w[l]||[];w[l].push({'gtm.start':new Date().getTime(),event:'gtm.js'});var f=d.getElementsByTagName(s)[0],j=d.createElement(s),dl=l!='dataLayer'?'&l='+l:'';j.async=true;j.src='https://www.googletagmanager.com/gtm.js?id='+i+dl;f.parentNode.insertBefore(j,f);})(window,document,'script','dataLayer','GTM-K279D39R'); Browse Preprints In Review Journals COVID-19 Preprints AJE Video Bytes Research Tools Research Promotion AJE Professional Editing AJE Rubriq About Preprint Platform In Review Editorial Policies Our Team Advisory Board Help Center Sign In Submit a Preprint Cite Share Download PDF Research Article A Computational Study on NACA 2412 Airfoil with a Leading-Edge Dimple MD REDWAN IQBAL, Zuairia Binte Noor Raha This is a preprint; it has not been peer reviewed by a journal. https://doi.org/ 10.21203/rs.3.rs-9235048/v1 This work is licensed under a CC BY 4.0 License Status: Posted Version 1 posted You are reading this latest preprint version Abstract Wing surface modifications, such as dimples, have gained significant research interest in aerodynamics due to their potential to enhance flow characteristics and improve the aerodynamic performance of airfoils. Inspiring from the mainstream principles used in golf ball design, the introduction of dimples on airfoils is a promising approach to enhance the aerodynamic efficiency without significant geometric complexity. In this study, a two-dimensional (2D) numerical analysis has been performed using “ANSYS Fluent” on the NACA 2412 airfoil with a chord length of 1m. The investigation is conducted at a free stream velocity of 50 m/s. A dimple is positioned on 30% of the chord from the leading edge, and the angle of attack (AOA) is varied from −3° to 18° with an interval of 3°. The numerical results demonstrate that the dimple-modified airfoil exhibits a higher lift coefficient (c l ), lower drag coefficient (c d ), and consequently an improved lift-to-drag ratio (c l /c d ) compared to the baseline airfoil. These findings suggest that the incorporation of dimples on an airfoil effectively enhances aerodynamic characteristics by delaying flow separation, particularly at higher angle of attack. Full Text Additional Declarations The authors declare no competing interests. Cite Share Download PDF Status: Posted Version 1 posted You are reading this latest preprint version Research Square lets you share your work early, gain feedback from the community, and start making changes to your manuscript prior to peer review in a journal. As a division of Research Square Company, we’re committed to making research communication faster, fairer, and more useful. We do this by developing innovative software and high quality services for the global research community. Our growing team is made up of researchers and industry professionals working together to solve the most critical problems facing scientific publishing. Also discoverable on Platform About Our Team In Review Editorial Policies Advisory Board Help Center Resources Author Services Accessibility API Access RSS feed Manage Cookie Preferences © Research Square 2026 | ISSN 2693-5015 (online) Privacy Policy Terms of Service Do Not Sell My Personal Information {"props":{"pageProps":{"initialData":{"identity":"rs-9235048","acceptedTermsAndConditions":true,"allowDirectSubmit":true,"archivedVersions":[],"articleType":"Research Article","associatedPublications":[],"authors":[{"id":612721665,"identity":"7d8df94b-d320-4b78-8478-c9f284661689","order_by":0,"name":"MD REDWAN IQBAL","email":"data:image/png;base64,iVBORw0KGgoAAAANSUhEUgAAAZAAAAAyAQMAAABI0h/eAAAABlBMVEX///8AAABVwtN+AAAACXBIWXMAAA7EAAAOxAGVKw4bAAAA8UlEQVRIiWNgGAWjYHACAyBm42Fjb2w48AHEZCdOC58cP8/hgw9ngLQwE6dFzlhyRlqyMQ+IT0iLeXvzNomfO8wSN9zIMZO2+bVNno+ZgfHDxxzcWmTOHCuT7D2TlrjhzBsz6dy+24ZtzAzMkjO34dYiIZFjdoO37VjihuNAW3J7bjMCtbAx8+LTIv/G7Obftv+JGw4AtVj23LYnrEWCx+w2bxubsWQH0PsMP24nEtbCk1b+W7aNDRLIvQ23k9uYGZvx+4X98GbDt23QqPzx57bt/Pbmgx8+4tGCChjbwGQDsepB4A8pikfBKBgFo2CkAADDXFKD/LJylgAAAABJRU5ErkJggg==","orcid":"https://orcid.org/0009-0009-7170-6186","institution":"Military Institute of Science and Technology","correspondingAuthor":true,"prefix":"","firstName":"MD","middleName":"REDWAN","lastName":"IQBAL","suffix":""},{"id":612721666,"identity":"c42773fe-7234-4302-a230-45095a5defe5","order_by":1,"name":"Zuairia Binte Noor Raha","email":"","orcid":"","institution":"Aviation and Aerospace University Bangladesh","correspondingAuthor":false,"prefix":"","firstName":"Zuairia","middleName":"Binte Noor","lastName":"Raha","suffix":""}],"badges":[],"createdAt":"2026-03-26 13:55:09","currentVersionCode":1,"declarations":{"humanSubjects":false,"vertebrateSubjects":false,"conflictsOfInterestStatement":false,"humanSubjectEthicalGuidelines":false,"humanSubjectConsent":false,"humanSubjectClinicalTrial":false,"humanSubjectCaseReport":false,"vertebrateSubjectEthicalGuidelines":false},"doi":"10.21203/rs.3.rs-9235048/v1","doiUrl":"https://doi.org/10.21203/rs.3.rs-9235048/v1","draftVersion":[],"editorialEvents":[],"editorialNote":"","failedWorkflow":false,"files":[{"id":105728524,"identity":"669caca2-86d7-4fd7-ab43-4a1bfc5a9e5a","added_by":"auto","created_at":"2026-03-30 11:12:05","extension":"pdf","order_by":1,"title":"","display":"","copyAsset":false,"role":"manuscript-pdf","size":600072,"visible":true,"origin":"","legend":"","description":"","filename":"AComputationalStudyonNACA2412AirfoilwithaLeadingEdgeDimple.pdf","url":"https://assets-eu.researchsquare.com/files/rs-9235048/v1_covered_a050074b-d2b3-426f-972e-2ca4f5b964e3.pdf"}],"financialInterests":"The authors declare no competing interests.","formattedTitle":"\u003cp\u003eA Computational Study on NACA 2412 Airfoil with a Leading-Edge Dimple\u003c/p\u003e","fulltext":[],"fulltextSource":"","fullText":"","funders":[],"hasAdminPriorityOnWorkflow":false,"hasManuscriptDocX":false,"hasOptedInToPreprint":true,"hasPassedJournalQc":"","hasAnyPriority":true,"hideJournal":true,"highlight":"","institution":"","isAcceptedByJournal":false,"isAuthorSuppliedPdf":true,"isDeskRejected":"","isHiddenFromSearch":false,"isInQc":false,"isInWorkflow":false,"isPdf":true,"isPdfUpToDate":true,"isWithdrawnOrRetracted":false,"journal":{"display":true,"email":"[email protected]","identity":"researchsquare","isNatureJournal":false,"hasQc":true,"allowDirectSubmit":true,"externalIdentity":"","sideBox":"","snPcode":"","submissionUrl":"/submission","title":"Research Square","twitterHandle":"researchsquare","acdcEnabled":true,"dfaEnabled":false,"editorialSystem":"","reportingPortfolio":"","inReviewEnabled":false,"inReviewRevisionsEnabled":true},"keywords":"","lastPublishedDoi":"10.21203/rs.3.rs-9235048/v1","lastPublishedDoiUrl":"https://doi.org/10.21203/rs.3.rs-9235048/v1","license":{"name":"CC BY 4.0","url":"https://creativecommons.org/licenses/by/4.0/"},"manuscriptAbstract":"\u003cp\u003eWing surface modifications, such as dimples, have gained significant research interest in aerodynamics due to their potential to enhance flow characteristics and improve the aerodynamic performance of airfoils. Inspiring from the mainstream principles used in golf ball design, the introduction of dimples on airfoils is a promising approach to enhance the aerodynamic efficiency without significant geometric complexity. In this study, a two-dimensional (2D) numerical analysis has been performed using “ANSYS Fluent” on the NACA 2412 airfoil with a chord length of 1m. The investigation is conducted at a free stream velocity of 50 m/s. A dimple is positioned on 30% of the chord from the leading edge, and the angle of attack (AOA) is varied from −3° to 18° with an interval of 3°. The numerical results demonstrate that the dimple-modified airfoil exhibits a higher lift coefficient (c\u003csub\u003el\u003c/sub\u003e), lower drag coefficient (c\u003csub\u003ed\u003c/sub\u003e), and consequently an improved lift-to-drag ratio (c\u003csub\u003el\u003c/sub\u003e/c\u003csub\u003ed\u003c/sub\u003e) compared to the baseline airfoil. 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