{"id":{"repo_id":"uiuc","oai_identifier":"oai:www.ideals.illinois.edu:2142/122027"},"canonical_url":"https://search.dev.ndltd.org/etd/uiuc/oai:www.ideals.illinois.edu:2142/122027","repository":{"repo_id":"uiuc","name":"University of Illinois - Urbana-Champaign","base_url":"https://www.ideals.illinois.edu/oai-pmh"},"display":{"title":"Multi-fidelity analysis and reduced-order modeling of wing-body aerodynamics","abstract":"Submission original under an indefinite embargo labeled 'Open Access'. The submission was exported from vireo on 2024-03-01 without embargo terms","abstract_html":"Submission original under an indefinite embargo labeled 'Open Access'. The submission was exported from vireo on 2024-03-01 without embargo terms","abstract_has_math":false,"creators":["Mahesh, Karthik"],"institution":"University of Illinois at Urbana-Champaign","degree_name":"M.S.","degree_level":"Thesis","degree_discipline":"Aerospace Engineering","degree_department":null,"school":null,"contributors":["Ansell, Phillip J"],"advisors":[],"committee_chairs":[],"committee_members":[],"year":2023,"date_issued":"2023-12","date_published":"2023-12","updated_at":"2026-07-22T22:25:00Z","subjects":["Aerodynamics","Reduced Order Modeling","Slender Body Theory","Wing Theory","Vortex Lattice Methods","Vortex Panel Methods","Panair","Avl","Lifting Line Theory"],"languages":["en","eng"],"rights":["Copyright 2023 Karthik Mahesh"],"rights_urls":[],"identifier_entries":[]},"links":{"outbound_url":"https://hdl.handle.net/2142/122027","outbound_label":"Handle","outbound_source":"dc:identifier"},"metadata_groups":[{"id":"people","label":"People","entries":[{"key":"dc:contributor","label":"Contributor","values":["Ansell, Phillip J"]},{"key":"dc:creator","label":"Author","values":["Mahesh, Karthik"]}]},{"id":"academic_context","label":"Academic Context","entries":[{"key":"dc:date","label":"Dc Date","values":["2023-12","2023-12-04"]},{"key":"dc:type","label":"Dc Type","values":["text"]},{"key":"thesis:degree_discipline","label":"Discipline","values":["Aerospace Engineering"]},{"key":"thesis:degree_level","label":"Degree Level","values":["Thesis"]},{"key":"thesis:degree_name","label":"Degree Name","values":["M.S."]},{"key":"thesis:institution_name","label":"Thesis Institution Name","values":["University of Illinois at Urbana-Champaign"]}]},{"id":"subjects_keywords","label":"Subjects and Keywords","entries":[{"key":"dc:subject","label":"Dc Subject","values":["Aerodynamics","Reduced Order Modeling","Slender Body Theory","Wing Theory","Vortex Lattice Methods","Vortex Panel Methods","Panair","Avl","Lifting Line Theory"]}]},{"id":"language_rights","label":"Language and Rights","entries":[{"key":"dc:language","label":"Dc Language","values":["en","eng"]},{"key":"dc:rights","label":"Dc Rights","values":["Copyright 2023 Karthik Mahesh"]}]},{"id":"identifiers","label":"Identifiers","entries":[{"key":"dc:identifier","label":"Identifier","values":["https://hdl.handle.net/2142/122027"]}]},{"id":"additional","label":"Additional Metadata","entries":[{"key":"dc:description","label":"Description","values":["Submission original under an indefinite embargo labeled 'Open Access'. The submission was exported from vireo on 2024-03-01 without embargo terms","The student, Karthik Mahesh, accepted the attached license on 2023-11-28 at 12:18.","The student, Karthik Mahesh, submitted this Thesis for approval on 2023-11-28 at 12:23.","This Thesis was approved for publication on 2023-12-04 at 11:13.","DSpace SAF Submission Ingestion Package generated from Vireo submission #20038 on 2024-03-01 at 13:15:09","The aerodynamic design benefits and configuration integration challenges of blended wing body (BWB) configurations over traditional tube-and-wing (TAW) designs have been thoroughly studied over the years. Research has shown that an intermediate approach, the lifting-center-body (LCB) configuration is optimal for regional and short-haul passenger aircraft, providing a significant aerodynamic benefit while reducing the integration complexity. This thesis aims to characterize the geometry and configuration aerodynamics of LCB aircraft across a range of wing-body blending. A variety of aerodynamic analysis methods are used to characterize the surface pressure and lift distributions and determine the sensitivity of various performance parameters to the degree of blending, and inform configuration design guidelines through these studies for aerodynamic design of LCB aircraft. It is postulated that spanload optimization strategies can provide significant reduction in induced drag for an LCB configuration over tube-and-wing configurations, and understanding the chordwise effects can further play an important role in the performance of these designs."]},{"key":"dc:format","label":"Dc Format","values":["application/pdf"]},{"key":"dc:title","label":"Title","values":["Multi-fidelity analysis and reduced-order modeling of wing-body aerodynamics"]}]}],"canonical_facts":{"dc:contributor":["Ansell, Phillip J"],"dc:creator":["Mahesh, Karthik"],"dc:date":["2023-12","2023-12-04"],"dc:description":["Submission original under an indefinite embargo labeled 'Open Access'. The submission was exported from vireo on 2024-03-01 without embargo terms","The student, Karthik Mahesh, accepted the attached license on 2023-11-28 at 12:18.","The student, Karthik Mahesh, submitted this Thesis for approval on 2023-11-28 at 12:23.","This Thesis was approved for publication on 2023-12-04 at 11:13.","DSpace SAF Submission Ingestion Package generated from Vireo submission #20038 on 2024-03-01 at 13:15:09","The aerodynamic design benefits and configuration integration challenges of blended wing body (BWB) configurations over traditional tube-and-wing (TAW) designs have been thoroughly studied over the years. Research has shown that an intermediate approach, the lifting-center-body (LCB) configuration is optimal for regional and short-haul passenger aircraft, providing a significant aerodynamic benefit while reducing the integration complexity. This thesis aims to characterize the geometry and configuration aerodynamics of LCB aircraft across a range of wing-body blending. A variety of aerodynamic analysis methods are used to characterize the surface pressure and lift distributions and determine the sensitivity of various performance parameters to the degree of blending, and inform configuration design guidelines through these studies for aerodynamic design of LCB aircraft. It is postulated that spanload optimization strategies can provide significant reduction in induced drag for an LCB configuration over tube-and-wing configurations, and understanding the chordwise effects can further play an important role in the performance of these designs."],"dc:format":["application/pdf"],"dc:identifier":["https://hdl.handle.net/2142/122027"],"dc:language":["en","eng"],"dc:rights":["Copyright 2023 Karthik Mahesh"],"dc:subject":["Aerodynamics","Reduced Order Modeling","Slender Body Theory","Wing Theory","Vortex Lattice Methods","Vortex Panel Methods","Panair","Avl","Lifting Line Theory"],"dc:title":["Multi-fidelity analysis and reduced-order modeling of wing-body aerodynamics"],"dc:type":["text"],"thesis:degree_discipline":["Aerospace Engineering"],"thesis:degree_level":["Thesis"],"thesis:degree_name":["M.S."],"thesis:institution_name":["University of Illinois at Urbana-Champaign"]},"updated_at":"2026-07-22T22:25:00Z"}