{"created":"2023-06-20T15:11:44.843982+00:00","id":41469,"links":{},"metadata":{"_buckets":{"deposit":"c3b6c087-f7ab-4a58-9751-4c0ac2b4a26a"},"_deposit":{"created_by":1,"id":"41469","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"41469"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00041469","sets":["1887:1893","1896:1898:1913:1916"]},"author_link":["452534","452542","452535","452528","452529","452532","452537","452538","452541","452531","452543","452530","452533","452536","452539","452540"],"item_3_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Experiments to ascertain the bluntness effect on attachment line transition of a yawed cylinder in hypersonic flow"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"2000-10","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"17","bibliographicPageStart":"1","bibliographicVolumeNumber":"753","bibliographic_titles":[{"bibliographic_title":"航空宇宙技術研究所資料"},{"bibliographic_title":"Technical Memorandum of National Aerospace Laboratory","bibliographic_titleLang":"en"}]}]},"item_3_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"先端を鋭く切り落とした斜め円柱模型と半球頭部を付加した模型の遷移試験を極超音速風洞において一様流Mach数7.1、円柱直径を基準長とした一様流Reynolds数0.1×10(exp 6)〜1.3×10(exp 6)の範囲で行った。仰角として30度、40度、50度の3条件で試験を実施した。その結果、無限斜め円柱を模擬した先端を鋭く切り落とした斜め円柱模型では、多に報告されている極超、超音速風洞における付着腺遷移データと比較的よい一致が得られた。半球頭部模型では、鈍頭部の効果によりα=50度でほぼ予測されたエントロピー層呑の領域に対応した遷移の抑制効果がみられたが、α=30度では予測をはるかに上回って遷移が抑制されることがわかった。α=40度における鈍頭効果は他の2ケースとまったく異なり鈍頭度が増すと遷移が早まる傾向を示した。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"Experiments on attachment line transition of two yawed cylinder models with a sharp and a hemisphere nose were conducted in a hypersonic wind tunnel. The tests were conducted at a free-stream Mach number of 7.1, free-stream Reynolds number based on cylinder diameter varying from 0.1 x 10(exp 6) to 1.3 x 10(exp 6) and angles of attack of 30 deg, 40 deg and 50 deg. Results for the sharp nose model tests matched those of other hypersonic wind tunnel tests. Tests for the hemisphere nose model at alpha = 30 deg showed nose bluntness to have a greater effect on transition than expected, based on the entropy layer swallowing effect, while at alpha = 50 deg, the effect was close to that expected. The bluntness effect at an angle of attack of 40 deg showed the opposite tendency to the other cases.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0028645000","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 TM-753","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":"0452-2982","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":"AN00314334","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 空力特性研究部"},{"subitem_text_value":"航空宇宙技術研究所 空力特性研究部"},{"subitem_text_value":"航空宇宙技術研究所 空力特性研究部"},{"subitem_text_value":"航空宇宙技術研究所 空力特性研究部"},{"subitem_text_value":"航空宇宙技術研究所 空力特性研究部"},{"subitem_text_value":"航空宇宙技術研究所 空力特性研究部"},{"subitem_text_value":"航空宇宙技術研究所 空力特性研究部"},{"subitem_text_value":"航空宇宙技術研究所 流体総合研究グループ"}]},"item_3_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Aerodynamics Division"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Aerodynamics Division"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Aerodynamics Division"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Aerodynamics Division"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Aerodynamics Division"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Aerodynamics Division"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Aerodynamics Division"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Fluid Science Research Group"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"藤井, 啓介"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"小山, 忠勇"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"津田, 尚一"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"平林, 則明"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"関根, 英夫"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"永井, 伸治"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"榊原, 盛三"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"穂積, 弘一"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Fujii, Keisuke","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Koyama, Tadao","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Tsuda, Shoichi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Hirabayashi, Noriaki","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Sekine, Hideo","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Nagai, Shinji","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Sakakibara, Seizo","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Hozumi, Koichi","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":"2020-01-27"}],"displaytype":"detail","filename":"naltm0000753.pdf","filesize":[{"value":"6.6 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"naltm0000753.pdf","url":"https://jaxa.repo.nii.ac.jp/record/41469/files/naltm0000753.pdf"},"version_id":"d5142fa8-ed9c-4930-8d4f-097855f1e5ff"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"鈍頭度効果","subitem_subject_scheme":"Other"},{"subitem_subject":"斜め円柱模型","subitem_subject_scheme":"Other"},{"subitem_subject":"半球頭部模型","subitem_subject_scheme":"Other"},{"subitem_subject":"付着線上境界層遷移","subitem_subject_scheme":"Other"},{"subitem_subject":"極超音速流","subitem_subject_scheme":"Other"},{"subitem_subject":"極超音速風洞実験","subitem_subject_scheme":"Other"},{"subitem_subject":"圧縮性流体","subitem_subject_scheme":"Other"},{"subitem_subject":"bluntness effect","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"yawed cylinder model","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"hemisphere nose model","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"attachment line transition","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"hypersonic flow","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"hypersonic wind tunnel test","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"compressible flow","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":"technical report","resourceuri":"http://purl.org/coar/resource_type/c_18gh"}]},"item_title":"極超音速流中斜円柱付着線上境界層遷移への鈍頭度の効果に関する実験","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"極超音速流中斜円柱付着線上境界層遷移への鈍頭度の効果に関する実験"}]},"item_type_id":"3","owner":"1","path":["1893","1916"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"41469","relation_version_is_last":true,"title":["極超音速流中斜円柱付着線上境界層遷移への鈍頭度の効果に関する実験"],"weko_creator_id":"1","weko_shared_id":1},"updated":"2023-06-20T19:11:10.696636+00:00"}