{"created":"2023-06-20T14:38:49.494653+00:00","id":5439,"links":{},"metadata":{"_buckets":{"deposit":"ccf87fb8-bfc9-4cea-a91a-f42b1da756f4"},"_deposit":{"created_by":1,"id":"5439","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"5439"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00005439","sets":["1887:1891","9:789:956:965"]},"author_link":["26383","26382"],"item_5_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Aerodynamic design of the NEXST-1 airplane"}]},"item_5_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"2009-02-27","bibliographicIssueDateType":"Issued"},"bibliographicVolumeNumber":"JAXA-SP-08-008","bibliographic_titles":[{"bibliographic_title":"宇宙航空研究開発機構特別資料: 小型超音速実験機（ロケット実験機）飛行実験データ解析完了報告"},{"bibliographic_title":"JAXA Special Publication","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":"小型超音速実験機（ロケット実験機）飛行実験データ解析完了報告会(平成20年7月10日. 東京大学山上会館)","subitem_description_type":"Other"}]},"item_5_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"JAXA developed a new aerodynamic design technology for a next generation SST in the National Experimental Supersonic Transport (NEXST) Program. In this program, four supersonic drag reduction concepts were applied into the aerodynamic design of the unmanned and scaled supersonic experimental airplane with no propulsion system called 'NEXST-1'. These concepts consisted of arrow planform, warped wing (optimum camber and twist), area-ruled body and supersonic natural laminar flow wing. Former three design concepts were derived to reduce pressure drag and the last one was originally developed to reduce friction drag. The aerodynamic design of the NEXST-1 airplane was conducted using a 'CFD-based inverse design method', which was originally developed in this program. Present four design concepts were also validated in JAXA's wind tunnel tests qualitatively. So, the flight test of the NEXST-1 airplane was expected to validate its design technology quantitatively. And good results were obtained as mentioned in present proceedings. Finally, the effect on applying the NEXST-1 aerodynamic design technology into the design of a real size SST was investigated. Consequently, improvement of about 13 % of the L/D of the real size SST was predicted comparing with the L/D of a Concorde-like configuration with no propulsion system.","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_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0064239003","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-08-008","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"}]},"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":"宇宙航空研究開発機構航空プログラムグループ"}]},"item_5_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"Aviation Program Group, Japan Aerospace Exploration Agency (JAXA)"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"吉田, 憲司"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Yoshida, Kenji","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":"64239003.pdf","filesize":[{"value":"15.1 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"64239003.pdf","url":"https://jaxa.repo.nii.ac.jp/record/5439/files/64239003.pdf"},"version_id":"6b2c0227-274a-46d9-aa87-dbc65a9e2e83"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"SST, Drag Reduction, Arrow Planform, Warp, Area-rule, Natural Laminar Flow","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":"ロケット実験機の空力設計概要","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"ロケット実験機の空力設計概要"}]},"item_type_id":"5","owner":"1","path":["965","1891"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"5439","relation_version_is_last":true,"title":["ロケット実験機の空力設計概要"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-21T08:15:02.068066+00:00"}