{"created":"2023-06-20T14:37:49.822139+00:00","id":4277,"links":{},"metadata":{"_buckets":{"deposit":"42724576-e303-40f9-828d-4c4f19b55b8a"},"_deposit":{"created_by":1,"id":"4277","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"4277"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00004277","sets":["1398:1530:1537","1543:1874:1881","1887:1891","9:789:888:896"]},"author_link":["18785","18780","18782","18781","18784","18783"],"item_5_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Development of Multi-Fidelity Aerodynamic Design Optimization Using Kriging Method for Supersonic Wing"}]},"item_5_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"2013-03-29","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"224","bibliographicPageStart":"219","bibliographicVolumeNumber":"JAXA-SP-12-010","bibliographic_titles":[{"bibliographic_title":"宇宙航空研究開発機構特別資料"},{"bibliographic_title":"JAXA Special Publication: Proceedings of 44th Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2012","bibliographic_titleLang":"en"}]}]},"item_5_description_14":{"attribute_name":"会議概要（会議名, 開催地, 会期, 主催者等）","attribute_value_mlt":[{"subitem_description":"第44回流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2012 (2012年7月5日-6日. 富山国際会議場大手町フォーラム), 富山市, 富山県","subitem_description_type":"Other"}]},"item_5_description_15":{"attribute_name":"会議概要（会議名, 開催地, 会期, 主催者等）（英）","attribute_value_mlt":[{"subitem_description":"44th Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2012 (July 5-6, 2012. Toyama International Conference Center), Toyama Japan","subitem_description_type":"Other"}]},"item_5_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"Multidisciplinary design optimization (MDO) is a practical key technology for the design of a supersonic transport (SST). The computational cost of MDO including aerodynamic design, however, should be expensive with high-fidelity CFD simulations. Therefore, surrogate models, such as response surface method or Kriging method are promising techniques for efficient MDO. Nevertheless, the computational cost will be still expensive to conduct the MDO using a surrogate model in practical time period because a lot of CFD calculations are required for global search. In this study, a fusion of the database with a low-cost/ low-fidelity solver and a high-cost/ high-fidelity solver in the Kriging model is considered to develop a more efficient global exploration method. A test problem with mathematical equation models and a practical aerodynamic design problem of a supersonic wing are carried out to investigate the efficiency of the proposed method. In t\"\"\" he supersonic wing design, a linear panel method and a structured Euler CFD solver are employed as a low-fidelity and a high-fidelity solver, respectively. As a result, the total computational cost is drastically reduced with the multi-fidelity method while the same optimum solutions can be explored as those with a single-fidelity optimization.","subitem_description_type":"Other"}]},"item_5_description_18":{"attribute_name":"内容記述","attribute_value_mlt":[{"subitem_description":"形態: カラー図版あり","subitem_description_type":"Other"}]},"item_5_description_19":{"attribute_name":"内容記述（英）","attribute_value_mlt":[{"subitem_description":"Physical characteristics: Original contains color illustrations","subitem_description_type":"Other"}]},"item_5_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0061958037","subitem_description_type":"Other"}]},"item_5_description_33":{"attribute_name":"レポート番号","attribute_value_mlt":[{"subitem_description":"レポート番号: JAXA-SP-12-010","subitem_description_type":"Other"}]},"item_5_publisher_8":{"attribute_name":"出版者","attribute_value_mlt":[{"subitem_publisher":"宇宙航空研究開発機構(JAXA)"}]},"item_5_publisher_9":{"attribute_name":"出版者（英）","attribute_value_mlt":[{"subitem_publisher":"Japan Aerospace Exploration Agency (JAXA)"}]},"item_5_source_id_21":{"attribute_name":"ISSN","attribute_value_mlt":[{"subitem_source_identifier":"1349-113X","subitem_source_identifier_type":"ISSN"}]},"item_5_source_id_24":{"attribute_name":"書誌レコードID","attribute_value_mlt":[{"subitem_source_identifier":"AA11984031","subitem_source_identifier_type":"NCID"}]},"item_5_text_6":{"attribute_name":"著者所属","attribute_value_mlt":[{"subitem_text_value":"首都大学東京大学院"},{"subitem_text_value":"宇宙航空研究開発機構航空本部機体システム研究グループ(JAXA)(APG)"},{"subitem_text_value":"首都大学東京"}]},"item_5_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"Graduate School, Tokyo Metropolitan University"},{"subitem_text_language":"en","subitem_text_value":"Aircraft Systems Research Group, Institute of Aeronautical Technology, Japan Aerospace Exploration Agency (JAXA)(APG)"},{"subitem_text_language":"en","subitem_text_value":"Tokyo Metropolitan University"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"高木, 秀寛"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"牧野, 好和"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"金崎, 雅博"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Takagi, Hidehiro","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Makino, Yoshikazu","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Kanazaki, Masahiro","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":"2020-01-16"}],"displaytype":"detail","filename":"61958037.pdf","filesize":[{"value":"1.2 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"61958037.pdf","url":"https://jaxa.repo.nii.ac.jp/record/4277/files/61958037.pdf"},"version_id":"ecda546e-04c7-449a-a147-a002ad2d5e43"}]},"item_language":{"attribute_name":"言語","attribute_value_mlt":[{"subitem_language":"jpn"}]},"item_resource_type":{"attribute_name":"資源タイプ","attribute_value_mlt":[{"resourcetype":"conference paper","resourceuri":"http://purl.org/coar/resource_type/c_5794"}]},"item_title":"Kriging法を用いたMulti-Fidelity空力最適設計法の検討と超音速機主翼設計への適用","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"Kriging法を用いたMulti-Fidelity空力最適設計法の検討と超音速機主翼設計への適用"}]},"item_type_id":"5","owner":"1","path":["896","1537","1881","1891"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"4277","relation_version_is_last":true,"title":["Kriging法を用いたMulti-Fidelity空力最適設計法の検討と超音速機主翼設計への適用"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-21T08:43:25.863296+00:00"}