{"created":"2023-06-20T15:07:24.219470+00:00","id":36774,"links":{},"metadata":{"_buckets":{"deposit":"da87addc-7605-4f93-b2c9-0cecca1aac3b"},"_deposit":{"created_by":1,"id":"36774","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"36774"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00036774","sets":["1887:1891","1896:1898:1913:1915"]},"author_link":["477530","477529","477528","477527"],"item_5_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Aerodynamic inverse optimization method for transonic wings"}]},"item_5_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1996-01","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"34","bibliographicPageStart":"29","bibliographicVolumeNumber":"30","bibliographic_titles":[{"bibliographic_title":"航空宇宙技術研究所特別資料"},{"bibliographic_title":"Special Publication of National Aerospace Laboratory","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":"航空宇宙技術研究所 7-9 Jun. 1995 東京 日本","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":"National Aerospace Laboratory 7-9 Jun. 1995 Tokyo Japan","subitem_description_type":"Other"}]},"item_5_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"遺伝的アルゴリズム(GA)を逆設計手法における目標圧力分布の最適化に適用した。GAでは導関数情報が不要なので、ロバストな空力最適化アルゴリズムが得られる。目標圧力分布が一旦得られると、対応する翼形形状がNavier-Stokesソルバと連結した逆設計コードにより算出される。現在の最適化アルゴリズムは有効であり、シミュレーションの展開によるスーパークリティカル翼は模擬進化(simulated evolution)により再設計されることを設計例は示した。","subitem_description_type":"Abstract"}]},"item_5_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"A Genetic Algorithm (GA) has been applied to optimize target pressure distributions for inverse design methods. Since GAs do not require any derivative information, the resulting aerodynamic optimization algorithm is robust. Once target pressure distributions are obtained, corresponding airfoil/wing geometries can be computed by an inverse design code coupled with a Navier-Stokes solver. Design examples indicate that the present optimization algorithm is efficient and that supercritical wing shapes are reproduced by the simulated evolution.","subitem_description_type":"Other"}]},"item_5_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0000294006","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: NAL SP-30","subitem_description_type":"Other"}]},"item_5_publisher_8":{"attribute_name":"出版者","attribute_value_mlt":[{"subitem_publisher":"航空宇宙技術研究所"}]},"item_5_publisher_9":{"attribute_name":"出版者（英）","attribute_value_mlt":[{"subitem_publisher":"National Aerospace Laboratory (NAL)"}]},"item_5_source_id_21":{"attribute_name":"ISSN","attribute_value_mlt":[{"subitem_source_identifier":"0289-260X","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":"AN10097345","subitem_source_identifier_type":"NCID"}]},"item_5_text_6":{"attribute_name":"著者所属","attribute_value_mlt":[{"subitem_text_value":"東北大学 工学研究科"},{"subitem_text_value":"航空宇宙技術研究所 空力性能部"}]},"item_5_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"Tohoku University Graduate School Division of Engineering"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Aircraft Aerodynamics Division"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"大林, 茂"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"高梨, 進"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Obayashi, Shigeru","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Takanashi, Susumu","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":"2020-02-10"}],"displaytype":"detail","filename":"nalsp0030006.pdf","filesize":[{"value":"564.3 kB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"nalsp0030006.pdf","url":"https://jaxa.repo.nii.ac.jp/record/36774/files/nalsp0030006.pdf"},"version_id":"cce384e3-02e5-4034-93a0-8039efd88ce9"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"翼形","subitem_subject_scheme":"Other"},{"subitem_subject":"空力逆最適化","subitem_subject_scheme":"Other"},{"subitem_subject":"スーパークリティカル翼","subitem_subject_scheme":"Other"},{"subitem_subject":"遺伝的アルゴリズム","subitem_subject_scheme":"Other"},{"subitem_subject":"圧力分布","subitem_subject_scheme":"Other"},{"subitem_subject":"模擬進化","subitem_subject_scheme":"Other"},{"subitem_subject":"シミュレーションモデル","subitem_subject_scheme":"Other"},{"subitem_subject":"遷音速翼","subitem_subject_scheme":"Other"},{"subitem_subject":"衝撃波","subitem_subject_scheme":"Other"},{"subitem_subject":"揚抗比","subitem_subject_scheme":"Other"},{"subitem_subject":"wing profile","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"aerodynamic inverse optimization method","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"supercritical wing","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"genetic algorithm","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"pressure distribution","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"simulated evolution","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"simulation model","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"transonic wing","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"shock wave","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"lift drag ratio","subitem_subject_language":"en","subitem_subject_scheme":"Other"}]},"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":"空力逆最適化による遷音速翼設計","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"空力逆最適化による遷音速翼設計"}]},"item_type_id":"5","owner":"1","path":["1891","1915"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"36774","relation_version_is_last":true,"title":["空力逆最適化による遷音速翼設計"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T21:31:55.117426+00:00"}