{"created":"2023-06-20T15:11:41.914829+00:00","id":41405,"links":{},"metadata":{"_buckets":{"deposit":"972dc2a6-3a3f-475e-8692-ec5b81917510"},"_deposit":{"created_by":1,"id":"41405","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"41405"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00041405","sets":["1887:1893","1896:1898:1913:1915"]},"author_link":["489891","489890","489894","489899","489898","489892","489895","489893","489896","489897"],"item_3_alternative_title_1":{"attribute_name":"その他のタイトル","attribute_value_mlt":[{"subitem_alternative_title":"超音速輸送機向け無推力実験機の自然層流翼上の遷移測定"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"2000-12","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"54","bibliographicPageStart":"51","bibliographicVolumeNumber":"48T","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_3_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 27-29 Sept.2000 東京 日本","subitem_description_type":"Other"}]},"item_3_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 27-29 Sept.2000 Tokyo Japan","subitem_description_type":"Other"}]},"item_3_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"超音速輸送機を目的とした無推力実験機の自然層流翼上の遷移測定をマッハ数2.0と1.2で行った。翼弦沿いに設置した熱フィルム流速計に対する出力信号の振幅中の摂動増加が層流から乱流境界層への遷移を示す。熱フィルム流速計およびPreston管による測定結果は遷移点が翼の半弦の下流に位置していることを明らかにした。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"Transition measurement on the natural laminar flow wing of non-powered experimental airplane for supersonic transport was conducted at Mach 2.0 and 1.2. Increase of perturbation in amplitude of output signals for hot-films placed along the wing chord indicates transition from laminar to turbulent boundary layer. Results by hot-film and Preston tubes proved that transition point is located downstream of the half chord of the wing.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0028637019","subitem_description_type":"Other"}]},"item_3_description_33":{"attribute_name":"レポート番号","attribute_value_mlt":[{"subitem_description":"レポート番号: NAL SP-48T","subitem_description_type":"Other"}]},"item_3_publisher_8":{"attribute_name":"出版者","attribute_value_mlt":[{"subitem_publisher":"航空宇宙技術研究所"}]},"item_3_publisher_9":{"attribute_name":"出版者（英）","attribute_value_mlt":[{"subitem_publisher":"National Aerospace Laboratory (NAL)"}]},"item_3_source_id_21":{"attribute_name":"ISSN","attribute_value_mlt":[{"subitem_source_identifier":"0289-260X","subitem_source_identifier_type":"ISSN"}]},"item_3_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_3_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":"航空宇宙技術研究所"},{"subitem_text_value":"航空宇宙技術研究所"},{"subitem_text_value":"航空宇宙技術研究所"}]},"item_3_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":"National Aerospace Laboratory"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"杉浦, 裕樹"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"吉田, 憲司"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"徳川, 直子"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"高木, 正平"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"西沢, 啓"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Sugiura, Hiroki","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Yoshida, Kenji","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Tokugawa, Naoko","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Takagi, Shohei","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Nishizawa, Akira","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":"nalsp0048020.pdf","filesize":[{"value":"667.8 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transport","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"nonpowered experimental airplane","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"natural laminar flow wing","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"turbulent boundary layer","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"transition point","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"wing chord","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"crossflow instability","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"optimum pressure distribution","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"compressible boundary layer","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"transition measurement","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":"technical report","resourceuri":"http://purl.org/coar/resource_type/c_18gh"}]},"item_title":"Transition measurement on the natural laminar flow wing of the non-powered experimental airplane for supersonic transport","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"Transition measurement on the natural laminar flow wing of the non-powered experimental airplane for supersonic transport","subitem_title_language":"en"}]},"item_type_id":"3","owner":"1","path":["1893","1915"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"41405","relation_version_is_last":true,"title":["Transition measurement on the natural laminar flow wing of the non-powered experimental airplane for supersonic transport"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T21:01:00.988717+00:00"}