{"created":"2023-06-20T15:08:36.750148+00:00","id":38100,"links":{},"metadata":{"_buckets":{"deposit":"e58fb5e5-2b26-4bb3-95eb-f61accc33c16"},"_deposit":{"created_by":1,"id":"38100","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"38100"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00038100","sets":["1887:1891","1896:1898:1913:1915"]},"author_link":["431701","431707","431700","431705","431704","431703","431702","431706"],"item_5_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Transition characteristics of non-powered experimental airplane at Mach 2"}]},"item_5_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"2002-01","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"30","bibliographicPageStart":"27","bibliographicVolumeNumber":"54","bibliographic_titles":[{"bibliographic_title":"航空宇宙技術研究所特別資料: 第28回境界層遷移の解明と制御研究会講演論文集"},{"bibliographic_title":"Special Publication of National Aerospace Laboratory: Proceedings of the 28th NAL Workshops on Investigation and Control of Boundary-Layer Transition","bibliographic_titleLang":"en"}]}]},"item_5_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"Transition on the natural laminar flow wing of a non-powered scaled supersonic experimental airplane was measured by hot-film sensors and an infrared camera at Mach 2. In order to supress crossflow instability which dominates the transition on the highly swept wing, the pressure falls very rapidly in the vicinity of leading edge of the wing, so as to minimize the crossflow velocity components. The unit Reynolds number had no effect on the transition Reynolds numbers of the wing. The transition Reynolds number was 0.8 million at 70 percent semi-spanwise location at Mach 2 at the angle of attack of 2 deg. Transition location in flight was estimated by conducting transition measurement in a quiet low Reynolds number wind tunnel and in a variable unit Reynolds number wind tunnel which has moderately low turbulence. The transition at 70 percent semi-spanwise position at the angle of attack of 2 deg at Mach 2 in flight was predicted to be located downstream of 60 percent chordwise position.","subitem_description_type":"Other"}]},"item_5_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0032827008","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: NAL SP-54","subitem_description_type":"Other"}]},"item_5_publisher_8":{"attribute_name":"出版者","attribute_value_mlt":[{"subitem_publisher":"航空宇宙技術研究所"}]},"item_5_publisher_9":{"attribute_name":"出版者（英）","attribute_value_mlt":[{"subitem_publisher":"National Aerospace Laboratory (NAL)"}]},"item_5_source_id_21":{"attribute_name":"ISSN","attribute_value_mlt":[{"subitem_source_identifier":"0289-260X","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":"AN10097345","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":"航空宇宙技術研究所"},{"subitem_text_value":"航空宇宙技術研究所"}]},"item_5_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"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":"高木, 正平"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"徳川, 直子"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"西沢, 啓"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Sugiura, Hiroki","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Takagi, Shohei","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Tokugawa, Naoko","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":"2020-01-24"}],"displaytype":"detail","filename":"nalsp0054008.pdf","filesize":[{"value":"1.9 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"nalsp0054008.pdf","url":"https://jaxa.repo.nii.ac.jp/record/38100/files/nalsp0054008.pdf"},"version_id":"e8b29a72-8f95-40b1-b3a5-e514cca8481b"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"超音速実験機","subitem_subject_scheme":"Other"},{"subitem_subject":"遷移特性","subitem_subject_scheme":"Other"},{"subitem_subject":"熱フィルム風速計","subitem_subject_scheme":"Other"},{"subitem_subject":"赤外カメラ","subitem_subject_scheme":"Other"},{"subitem_subject":"圧力分布","subitem_subject_scheme":"Other"},{"subitem_subject":"横流れ","subitem_subject_scheme":"Other"},{"subitem_subject":"風洞","subitem_subject_scheme":"Other"},{"subitem_subject":"supersonic experimental airplane","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"transition characteristic","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"hot film anemometer","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"infrared camera","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"pressure distribution","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"cross flow","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"wind tunnel","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":"マッハ2における小型超音速実験機の遷移特性","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"マッハ2における小型超音速実験機の遷移特性"}]},"item_type_id":"5","owner":"1","path":["1891","1915"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"38100","relation_version_is_last":true,"title":["マッハ2における小型超音速実験機の遷移特性"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T22:45:12.012497+00:00"}