{"created":"2023-06-20T14:39:05.578659+00:00","id":5766,"links":{},"metadata":{"_buckets":{"deposit":"19e8b2c0-07bb-4a59-95fd-ea9a284d8c3d"},"_deposit":{"created_by":1,"id":"5766","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"5766"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00005766","sets":["1887:1891","9:789:998:1005"]},"author_link":["476967","476965","476968","476963","476964","476966"],"item_5_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"2007-03-30","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"315","bibliographicPageStart":"310","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":"The numerical simulation of a Mach 2.0 scaled supersonic experimental airplane is conducted with the consideration of the integration between airframe and engine nacelles. A three-dimensional Euler CFD (Computational Fluid Dynamics) code with an overset-grids technique is adopted for solving the flow-field around a complex airplane configuration. The calculated pressure distributions are compared with wind tunnel test data and show good agreement with them. The aerodynamic design tool which combines the CFD code with an optimization technique for drag minimization is developed. At first, it is applied to an axisymmetrical body in order to validate this design tool. The result shows that the optimized body geometry agrees well with the Sears-Haack body. Next, it is applied to two bodies under a wing-body configuration. The pressure drag of the optimized configurations is about nine percent lower than that of the Sears-Haack body maintaining their final volumes.","subitem_description_type":"Other"}]},"item_5_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0063609035","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":"航空宇宙技術研究所"},{"subitem_text_value":"航空宇宙技術研究所"},{"subitem_text_value":"ヴァイナス"}]},"item_5_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory"},{"subitem_text_language":"en","subitem_text_value":"VINAS Co. Ltd."}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"牧野, 好和"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"岩宮, 敏幸"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Lei, Zhong"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Makino, Yoshikazu","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Iwamiya, Toshiyuki","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Lei, Zhong","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":"63609035.pdf","filesize":[{"value":"2.6 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"63609035.pdf","url":"https://jaxa.repo.nii.ac.jp/record/5766/files/63609035.pdf"},"version_id":"16178f2a-b220-4b4e-b70d-8a82cfb90e3d"}]},"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":"実験機","subitem_subject_scheme":"Other"},{"subitem_subject":"計算流体力学","subitem_subject_scheme":"Other"},{"subitem_subject":"形状最適化","subitem_subject_scheme":"Other"},{"subitem_subject":"ナセル","subitem_subject_scheme":"Other"},{"subitem_subject":"空力設計","subitem_subject_scheme":"Other"},{"subitem_subject":"空力特性","subitem_subject_scheme":"Other"},{"subitem_subject":"設計最適化","subitem_subject_scheme":"Other"},{"subitem_subject":"圧力抗力","subitem_subject_scheme":"Other"},{"subitem_subject":"胴翼構成","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":"research aircraft","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"computational fluid dynamics","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"shape optimization","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"nacelle","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"aerodynamic design","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"aerodynamic characteristic","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"design optimization","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"pressure drag","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"body-wing configuration","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 nacelle shape optimization for NAL's experimental airplane","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"Aerodynamic nacelle shape optimization for NAL's experimental airplane","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":"5766","relation_version_is_last":true,"title":["Aerodynamic nacelle shape optimization for NAL's experimental airplane"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T21:34:08.540272+00:00"}