{"created":"2023-06-20T14:39:06.285729+00:00","id":5777,"links":{},"metadata":{"_buckets":{"deposit":"d0c57b19-a460-4400-964a-89dc4c1ea43e"},"_deposit":{"created_by":1,"id":"5777","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"5777"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00005777","sets":["1887:1891","9:789:998:1005"]},"author_link":["477008","477009"],"item_5_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"2007-03-30","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"396","bibliographicPageStart":"390","bibliographicVolumeNumber":"JAXA-SP-06-029E","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 International Workshops on Numerical Simulation Technology for Design of Next Generation Supersonic Civil Transport (SST-CFD Workshop)","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":"SST-CFDワークショップ.次世代超音速機の数値シミュレーション利用技術に関する国際ワークショップ 航空宇宙技術研究所 20000117-20000119 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":"SST-CFD Workshop. International Workshops on Numerical Simulation Technology for Design of Next Generation Supersonic Civil Transport National Aerospace Laboratory 20000117-20000119 Tokyo Japan","subitem_description_type":"Other"}]},"item_5_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"Aerodynamic design of Natural Laminar Flow (NLF) for supersonic aircraft wings was conducted by using 3-D CFD (Computational Fluid Dynamics) analysis and boundary layer stability analysis. There are two main subjects for NLF wing design. One is that the wing of the sub-scaled unmanned supersonic experimental aircraft of National Aerospace Laboratory (NAL) was designed to improve the L/D (Lift to Drag) ratio. This wing sections were designed especially to reduce skin friction drag which amounts to nearly half of the total drag. For this purpose, we designed the wing sections to remain laminar flow as far as possible using 3-D CFD solver and 3-D laminar boundary layer stability analysis code and 2-D inverse design method. The other is that the simple sweep-back wing was designed to delay a transition due to cross flow instability in consideration of spanwise pressure distribution. (This design concept of NLF is patented.)","subitem_description_type":"Other"}]},"item_5_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0063609046","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-06-029E","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":"川崎重工業 岐阜技術研究所"}]},"item_5_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"Kawasaki Heavy Industries Ltd. Gifu Technical Institute"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"生越, 博景"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Ogoshi, Hirokage","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":"63609046.pdf","filesize":[{"value":"1.6 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"63609046.pdf","url":"https://jaxa.repo.nii.ac.jp/record/5777/files/63609046.pdf"},"version_id":"66516b47-4dd8-4c12-8fe2-7362fbcbc73e"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"超音速機","subitem_subject_scheme":"Other"},{"subitem_subject":"航空機設計","subitem_subject_scheme":"Other"},{"subitem_subject":"層流翼型","subitem_subject_scheme":"Other"},{"subitem_subject":"計算流体力学","subitem_subject_scheme":"Other"},{"subitem_subject":"空力設計","subitem_subject_scheme":"Other"},{"subitem_subject":"実験機","subitem_subject_scheme":"Other"},{"subitem_subject":"揚抗比","subitem_subject_scheme":"Other"},{"subitem_subject":"層流境界層","subitem_subject_scheme":"Other"},{"subitem_subject":"3次元モデル","subitem_subject_scheme":"Other"},{"subitem_subject":"後退翼","subitem_subject_scheme":"Other"},{"subitem_subject":"圧力分布","subitem_subject_scheme":"Other"},{"subitem_subject":"supersonic aircraft","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"aircraft design","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"laminar flow airfoil","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"computational fluid dynamics","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"aerodynamic design","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"research aircraft","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"lift drag ratio","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"laminar boundary layer","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"three dimensional model","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"sweptback wing","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"pressure distribution","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":"conference paper","resourceuri":"http://purl.org/coar/resource_type/c_5794"}]},"item_title":"Aerodynamic design of Natural Laminar Flow supersonic aircraft wings","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"Aerodynamic design of Natural Laminar Flow supersonic aircraft wings","subitem_title_language":"en"}]},"item_type_id":"5","owner":"1","path":["1005","1891"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"5777","relation_version_is_last":true,"title":["Aerodynamic design of Natural Laminar Flow supersonic aircraft wings"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T21:33:56.059592+00:00"}