{"id":19601,"date":"2025-05-12T10:49:32","date_gmt":"2025-05-12T10:49:32","guid":{"rendered":"https:\/\/aerospacerepository.org\/?p=19601"},"modified":"2025-09-10T10:59:35","modified_gmt":"2025-09-10T10:59:35","slug":"aerodynamic-analysis-of-aircraft-wings-using-a-coupled-pm-bl-approach","status":"publish","type":"post","link":"https:\/\/aerospacerepository.org\/index.php\/2025\/05\/12\/aerodynamic-analysis-of-aircraft-wings-using-a-coupled-pm-bl-approach\/","title":{"rendered":"Aerodynamic analysis of aircraft wings using a coupled PM-BL approach"},"content":{"rendered":"\n<p><strong>Lipeng Zhu, Changchuan Xie, Yang Meng<\/strong><\/p>\n\n\n\n<p><strong>DOI Number: https:\/\/doi.org\/10.82439\/ceas-ifasd-2024-041<\/strong><\/p>\n\n\n\n<p><strong>Conference number: IFASD-2024-041<\/strong><\/p>\n\n\n\n<p>The objective of this paper is to develop an aerodynamic model suitable for aeroelastic analysis with low computational cost and sufficient fidelity. The physics-based reduce order model is based on the unsteady inviscid Panel Method (PM), selected for its low computation time. Viscous effects are modeled with two-dimensional unsteady high-fidelity boundary layer calculations at various sections along the span and incorporated as an effective shape boundary condition correction inside the PM. The viscous sectional data are calculated with two-dimensional differential boundary layer equations to allow viscous effects to be included for a more accurate maximum lift coefficient and spanload evaluations. These viscous corrections are coupled through a modified displacement thickness distribution coupling method for 2D boundary layer sectional data.<\/p>\n\n\n\n<p><a href=\"https:\/\/aerospacerepository.org\/wp-content\/uploads\/2025\/05\/41.pdf\">Read the full paper here<\/a><\/p>\n\n\n\n<p><\/p>\n","protected":false},"excerpt":{"rendered":"<p><b>Lipeng Zhu, Changchuan Xie, Yang Meng<\/b><\/p>\n<p>DOI Number: https:\/\/doi.org\/10.82439\/ceas-ifasd-2024-041<\/p>\n<p>Conference number: IFASD-2024-041<\/p>\n","protected":false},"author":2,"featured_media":0,"comment_status":"open","ping_status":"open","sticky":false,"template":"","format":"standard","meta":{"footnotes":""},"categories":[993,3027,3022],"tags":[2483,3301,1312],"class_list":["post-19601","post","type-post","status-publish","format-standard","hentry","category-events","category-aeroservoelasticity-1-ifasd-2024","category-ifasd-2024","tag-panel-method","tag-unsteady-boundary-layer-method","tag-viscous-correction","category-993","category-3027","category-3022","description-off"],"_links":{"self":[{"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/19601","targetHints":{"allow":["GET"]}}],"collection":[{"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts"}],"about":[{"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/types\/post"}],"author":[{"embeddable":true,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/users\/2"}],"replies":[{"embeddable":true,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/comments?post=19601"}],"version-history":[{"count":3,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/19601\/revisions"}],"predecessor-version":[{"id":20419,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/19601\/revisions\/20419"}],"wp:attachment":[{"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/media?parent=19601"}],"wp:term":[{"taxonomy":"category","embeddable":true,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/categories?post=19601"},{"taxonomy":"post_tag","embeddable":true,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/tags?post=19601"}],"curies":[{"name":"wp","href":"https:\/\/api.w.org\/{rel}","templated":true}]}}