Blended Wing Body Design in UNICADO

Blended Wing Body Design in UNICADO | 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PDF Research Article Blended Wing Body Design in UNICADO Philipp Hansmann, Eike Stumpf This is a preprint; it has not been peer reviewed by a journal. https://doi.org/ 10.21203/rs.3.rs-7011252/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 This paper presents a sizing and design methodology for the conceptual phase of blended wing body (BWB) aircraft. The proposed design framework provides a sized and trimmed lifting body with predefined longitudinal stability. Starting from a specified sizing point and cabin geometry, a four-segment lifting body planform is constructed. The fuselage segment is defined by encasing the cabin, while the remaining lifting surface area is allocated to the wing, sized according to required wing loading. The methodology incorporates distinct stabilization and trimming processes. The aerodynamic center is primarily determined by the lifting body planform, allowing an independent definition of the aerodynamic behavior based on airfoil selection. To achieve desired stability margins, the wing is relocated in relation to the fuselage in an iterative process. To minimize vortex lattice method executions, a Gaussian Process Regression serves as a surrogate model in determining aerodynamic center location.Tailored fuselage airfoils provide both positive pitching moments and lift through variations in camberline and thickness distribution. The iterative trimming process ensures that aerodynamic behavior meets design requirements while fitting the cabin within the fuselage airfoils at all times. Ultimately, this methodology yields a sized and trimmed BWB configuration with well-defined stability characteristics, enabling effective exploration of the BWB design space. Blended Wing Body Conceptual Aircraft Design Gaussian Process Regression Stability Full Text Additional Declarations No competing interests reported. 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-7011252","acceptedTermsAndConditions":true,"allowDirectSubmit":true,"archivedVersions":[],"articleType":"Research Article","associatedPublications":[],"authors":[{"id":480167399,"identity":"16611744-307e-447b-930f-9f3e4ff99128","order_by":0,"name":"Philipp Hansmann","email":"data:image/png;base64,iVBORw0KGgoAAAANSUhEUgAAAZAAAAAyAQMAAABI0h/eAAAABlBMVEX///8AAABVwtN+AAAACXBIWXMAAA7EAAAOxAGVKw4bAAABD0lEQVRIiWNgGAWjYBACAxiDn5m5ASHCCGYn4Nci2QxRJkG8FoMDxGoxZz97+NONmjt5xscZ2z4w7jlcZ87A/PDDzx02eQzsyQewabHsyUuTzjn2rNjsMGPzDIZnhyUsG9iMJXvPpBUz8DzDao3BgRwz5hy2w4nbgFoYGA7cljC4/8BAmrHtcGKDRI4BVi3n3xh/zvl3OHFzM0zLAfbPvxnb/gO15H/AquVGjoF0LtDMDcxwLTxmQFsOgGzBHmI33phJ5/YdTpwBcljCgf+SGw7wlFn2tiUntvE8w+GwHKDDvh1O7O8/fJjhw4E0fqDDNt/42WaX2M+e/ACrNSgAJYTYCKsfBaNgFIyCUYADAAArMmh4FEsa8gAAAABJRU5ErkJggg==","orcid":"","institution":"RWTH Aachen University","correspondingAuthor":true,"prefix":"","firstName":"Philipp","middleName":"","lastName":"Hansmann","suffix":""},{"id":480167400,"identity":"45e5cc9f-8280-49fb-a32c-1ad6f882e35d","order_by":1,"name":"Eike Stumpf","email":"","orcid":"","institution":"RWTH Aachen University","correspondingAuthor":false,"prefix":"","firstName":"Eike","middleName":"","lastName":"Stumpf","suffix":""}],"badges":[],"createdAt":"2025-06-30 13:53:20","currentVersionCode":1,"declarations":"","doi":"10.21203/rs.3.rs-7011252/v1","doiUrl":"https://doi.org/10.21203/rs.3.rs-7011252/v1","draftVersion":[],"editorialEvents":[],"editorialNote":"","failedWorkflow":false,"files":[{"id":86122621,"identity":"93cbd6e6-fb06-4eea-ba5d-27e46b9e82cc","added_by":"auto","created_at":"2025-07-07 04:20:11","extension":"pdf","order_by":1,"title":"","display":"","copyAsset":false,"role":"manuscript-pdf","size":1896649,"visible":true,"origin":"","legend":"","description":"","filename":"Hansmann2005BlendedWingBodyInUNICADO.pdf","url":"https://assets-eu.researchsquare.com/files/rs-7011252/v1_covered_052d9d22-478e-447d-804a-cab5d90de71d.pdf"}],"financialInterests":"No competing interests reported.","formattedTitle":"Blended Wing Body Design in UNICADO","fulltext":[],"fulltextSource":"","fullText":"","funders":[],"hasAdminPriorityOnWorkflow":false,"hasManuscriptDocX":false,"hasOptedInToPreprint":true,"hasPassedJournalQc":"","hasAnyPriority":false,"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":"Blended Wing Body, Conceptual Aircraft Design, Gaussian Process Regression, Stability","lastPublishedDoi":"10.21203/rs.3.rs-7011252/v1","lastPublishedDoiUrl":"https://doi.org/10.21203/rs.3.rs-7011252/v1","license":{"name":"CC BY 4.0","url":"https://creativecommons.org/licenses/by/4.0/"},"manuscriptAbstract":"This paper presents a sizing and design methodology for the conceptual phase of blended wing body (BWB) aircraft. 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