{"created":"2023-06-20T14:39:05.319029+00:00","id":5762,"links":{},"metadata":{"_buckets":{"deposit":"cf317fcf-ddbc-4741-b6b6-0519e3ef36e7"},"_deposit":{"created_by":1,"id":"5762","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"5762"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00005762","sets":["1887:1891","9:789:998:1005"]},"author_link":["476931","476938","476937","476932","476934","476936","476933","476935"],"item_5_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"2007-03-30","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"285","bibliographicPageStart":"280","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":"Boundary layer transition characteristics of the scaled supersonic experimental airplane was numerically analyzed to confirm its Natural Laminar Flow (NLF) wing design. Using conventional incompressible and newly developed compressible transition prediction codes based on an e(sup N) method, the NLF characteristics were well confirmed though the following results. (1) The step function type target pressure distribution applied in the NLF wing design was found to be optimum (2) Comparing the transition N value estimated by the compressible code with experimental results obtained by NASA, wide laminar region of the NLF wing was expected. (3) Laminar boundary layer profiles estimated by a Navier-Stokes code led to smaller N value than one by the compressible boundary layer code. (4) No transition due to attachment-line contamination was predicted.","subitem_description_type":"Other"}]},"item_5_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0063609031","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 次世代航空機プロジェクト推進センター"},{"subitem_text_value":"航空宇宙技術研究所 計算科学研究部"},{"subitem_text_value":"航空宇宙技術研究所"},{"subitem_text_value":"三向ソフトウェア開発"}]},"item_5_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Advanced Technology Aircraft Project Center"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Computational Science Division"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory"},{"subitem_text_language":"en","subitem_text_value":"Sanko Software Ltd."}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"吉田, 憲司"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"岩宮, 敏幸"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"上田, 良稲"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"石川, 敬掲"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Yoshida, Kenji","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Iwamiya, Toshiyuki","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Ueda, Yoshine","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Ishikawa, Hiroaki","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":"63609031.pdf","filesize":[{"value":"3.2 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"63609031.pdf","url":"https://jaxa.repo.nii.ac.jp/record/5762/files/63609031.pdf"},"version_id":"e73a45bb-3722-4b11-8f4a-530b19059b47"}]},"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":"境界層遷移","subitem_subject_scheme":"Other"},{"subitem_subject":"圧力分布","subitem_subject_scheme":"Other"},{"subitem_subject":"層流境界層","subitem_subject_scheme":"Other"},{"subitem_subject":"圧縮性境界層","subitem_subject_scheme":"Other"},{"subitem_subject":"圧縮性効果","subitem_subject_scheme":"Other"},{"subitem_subject":"設計最適化","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":"boundary layer transition","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"pressure distribution","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"laminar boundary layer","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"compressible boundary layer","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"compressibility effect","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"design optimization","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":"Boundary layer transition analysis of the scaled supersonic experimental airplane","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"Boundary layer transition analysis of the scaled supersonic 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":"5762","relation_version_is_last":true,"title":["Boundary layer transition analysis of the scaled supersonic experimental airplane"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T21:34:12.701797+00:00"}