{"created":"2023-06-20T14:54:12.171160+00:00","id":22483,"links":{},"metadata":{"_buckets":{"deposit":"2a9d04bf-d116-41f9-a54e-2b4e1f92ed5f"},"_deposit":{"created_by":1,"id":"22483","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"22483"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00022483","sets":["1887:1888"]},"author_link":["210854","210853","210855","210851","210852","210850"],"item_7_alternative_title_1":{"attribute_name":"その他のタイトル","attribute_value_mlt":[{"subitem_alternative_title":"Mixed-Fidelityによる効率的設計探査法の超音速主翼設計への適用"}]},"item_7_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"2014-01-11","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"99","bibliographicPageStart":"85","bibliographicVolumeNumber":"67","bibliographic_titles":[{},{"bibliographic_title":"Procedia Engineering","bibliographic_titleLang":"en"}]}]},"item_7_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"Multidisciplinary design optimizations are practical key technology for the efficient design of a supersonic transport (SST). However, the computational cost should be expensive with high fidelity flow solver. Thus, the surrogate models such as the Kriging method is one of the promising technique. On the other hand, the computational cost still expensive, because a lot of CFD runs is required to achieve global search with high-fidelity solver. In this study, to develop higher efficient global exploration method, it was considered that a fusion of the database by a low cost/low fidelity solver and a high cost/high fidelity solve using Kriging model. A test problem and a design problem of the wing of SST was carried out to investigate the efficiency of the proposed method. In the design of the SST, the liner potential solver and the structured Euler solver was employed. According to the result, the total computational cost was drastically reduced while the same optimum solution can be explored as a single-fidelity optimization.","subitem_description_type":"Other"}]},"item_7_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: PA1420033000","subitem_description_type":"Other"}]},"item_7_publisher_9":{"attribute_name":"出版者（英）","attribute_value_mlt":[{"subitem_publisher":"Elsevier"}]},"item_7_relation_25":{"attribute_name":"DOI","attribute_value_mlt":[{"subitem_relation_name":[{"subitem_relation_name_text":"info:doi/10.1016/j.proeng.2013.12.008"}],"subitem_relation_type":"isVersionOf","subitem_relation_type_id":{"subitem_relation_type_id_text":"http://dx.doi.org/10.1016/j.proeng.2013.12.008","subitem_relation_type_select":"DOI"}}]},"item_7_rights_28":{"attribute_name":"権利","attribute_value_mlt":[{"subitem_rights":"Copyright (C)2013, Elsevier. || NOTICE: this is the author's version of a work that was accepted for publication in Procedia Engineering. Changes resulting from the publishing process, such as peer review, editing, corrections, structural formatting, and other quality control mechanisms may not be reflected in this document. Changes may have been made to this work since it was submitted for publication. A definitive version was subsequently published in PUBLICATION, Volume 67, 2013, DOI:10.1016/j.proeng.2013.12.008"}]},"item_7_source_id_21":{"attribute_name":"ISSN","attribute_value_mlt":[{"subitem_source_identifier":"1877-7058","subitem_source_identifier_type":"ISSN"}]},"item_7_text_6":{"attribute_name":"著者所属","attribute_value_mlt":[{"subitem_text_value":"首都大学東京"},{"subitem_text_value":"首都大学東京"},{"subitem_text_value":"宇宙航空研究開発機構航空本部(JAXA)"}]},"item_7_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"Tokyo Metropolitan University"},{"subitem_text_language":"en","subitem_text_value":"Tokyo Metropolitan University"},{"subitem_text_language":"en","subitem_text_value":"Institute of Aeronautical Technology, Japan Aerospace Exploration Agency (JAXA)"}]},"item_7_version_type_30":{"attribute_name":"著者版フラグ","attribute_value_mlt":[{"subitem_version_resource":"http://purl.org/coar/version/c_ab4af688f83e57aa","subitem_version_type":"AM"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"金崎, 雅博"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"高木, 秀寛"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"牧野, 好和"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Kanazaki, Masahiro","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Takagi, Hidehiro","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Makino, Yoshikazu","creatorNameLang":"en"}],"nameIdentifiers":[{}]}]},"item_files":{"attribute_name":"ファイル情報","attribute_type":"file","attribute_value_mlt":[{"accessrole":"open_date","date":[{"dateType":"Available","dateValue":"2020-01-22"}],"displaytype":"detail","filename":"PA1420033.pdf","filesize":[{"value":"1.1 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"PA1420033.pdf","url":"https://jaxa.repo.nii.ac.jp/record/22483/files/PA1420033.pdf"},"version_id":"cf5abbe9-99a0-4e23-bbf9-f8c990c64fb9"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"Multi-Fidelity Design","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"Kriging Method","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"Supersonic Aircraft","subitem_subject_language":"en","subitem_subject_scheme":"Other"}]},"item_language":{"attribute_name":"言語","attribute_value_mlt":[{"subitem_language":"eng"}]},"item_resource_type":{"attribute_name":"資源タイプ","attribute_value_mlt":[{"resourcetype":"journal article","resourceuri":"http://purl.org/coar/resource_type/c_6501"}]},"item_title":"Mixed-fidelity Efficient Global Optimization Applied to Design of Supersonic Wing","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"Mixed-fidelity Efficient Global Optimization Applied to Design of Supersonic Wing","subitem_title_language":"en"}]},"item_type_id":"7","owner":"1","path":["1888"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"22483","relation_version_is_last":true,"title":["Mixed-fidelity Efficient Global Optimization Applied to Design of Supersonic Wing"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-21T03:20:24.528449+00:00"}