{"created":"2023-06-20T15:03:02.036345+00:00","id":32132,"links":{},"metadata":{"_buckets":{"deposit":"8771759b-b7c8-4001-a217-7e61a83e926d"},"_deposit":{"created_by":1,"id":"32132","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"32132"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00032132","sets":["1887:1890","1896:1898:1899:1910"]},"author_link":["407438","407436","407437","407439"],"item_9_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Experimental Study on the Characteristics of an Isolated Swept-Back Aerofoil with Two Parallel Side-Walls"}]},"item_9_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1973-07","bibliographicIssueDateType":"Issued"},"bibliographicIssueNumber":"3","bibliographicPageEnd":"793","bibliographicPageStart":"763","bibliographicVolumeNumber":"9","bibliographic_titles":[{"bibliographic_title":"東京大学宇宙航空研究所報告"}]}]},"item_9_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"航空原動機の軸流圧縮機,タービンにおける後退翼列の空力的特性を基礎的に調べることを目的として,平行側壁をもつ流路におかれた単独後退翼に対して実験を行なった.本実験においては,主流方向に同一の翼断面形状(NACA 65-810,翼弦長:60mm)をもつ翼を用いて,それぞれ三種類のアスペクト比(AR=l,2,3)および後退角(φ=0°,30°,45°)の場合において,翼面圧力分布を測定し,また油膜法により翼面上のフロー・パターンを観察した.その結果を要約すると次の通りである.まず迎角が小さい場合には,翼面圧力分布の翼幅方向の変化は,ARが小さくφが大きいほど大きいが,局所揚力の翼幅方向の変化は小さい.また局所揚力および翼全体の揚力は,φが大きいほどその大きさおよび揚力こう配が低下するが,ARにはほとんど無関係である.迎角を増してゆくと,下流側の翼部分から失速し始め,迎角の増加とともに失速が上流側翼部分に進行する,特にAR,がいずれも大きい場合には,翼背面を斜めに横切るpart-span渦が生じるようになる.このとき,局所揚力は,迎角の増加によって失速する直前に,大きな正の揚力こう配をもって増大するようになり,それはAR,φが大きい場合ほど著しい.これに対し翼全体の揚力はゆるやかに変化し,局所揚力特性や二次元揚力特性に見られる失速による急激な変化は見られない.","subitem_description_type":"Abstract"}]},"item_9_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"The aerodynamic characteristics of an isolated swept-back aerofoil which spans between two parallel side-walls were examined experimentally, by measuring the distributions of static pressure over the aerofoil and by visualizing the flow pattern on its surfaces. The experiment was carried out for the cases in which the aspect ratio of the aerofoil is 1, 2, 3 and the angle of sweep is 0°, 30°, 45°respectively. The profile of the aerofoil is NACA 65-810 in the streamwise section, and the Reynolds number in the test is kept constant 1.7×10^5. The results obtained are summarized as follows; (1) In the range of samall angle of attack, the spanwise variation of the pressure distributions on the aerofoil is remarkable for smaller aspect ratio and for larger sweep angle, but the local lift is almost constant over the whole span. The local and total lifts are nearly independent of the aspect ratio. (2) As the angle of attack increases, the stalled portion due to the leading edge separation spreads from the downstream side of the swept aerofoil to the upstream. Particularly when the aspect rario and the angle of sweep are both large, so-called part-span vortex is observed crossing diagonally over the aerofoil. The total lift changes gradually against the change of the angle of attack, although the local lift tends to increase abruptly just before falling into stall.","subitem_description_type":"Other"}]},"item_9_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: SA0125254000","subitem_description_type":"Other"}]},"item_9_publisher_8":{"attribute_name":"出版者","attribute_value_mlt":[{"subitem_publisher":"東京大学宇宙航空研究所"}]},"item_9_source_id_21":{"attribute_name":"ISSN","attribute_value_mlt":[{"subitem_source_identifier":"0563-8100","subitem_source_identifier_type":"ISSN"}]},"item_9_source_id_24":{"attribute_name":"書誌レコードID","attribute_value_mlt":[{"subitem_source_identifier":"AN00161914","subitem_source_identifier_type":"NCID"}]},"item_9_text_6":{"attribute_name":"著者所属","attribute_value_mlt":[{"subitem_text_value":"東京大学宇宙航空研究所"},{"subitem_text_value":"東京大学宇宙航空研究所"}]},"item_9_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"Institute of Space and Aeronautical Science"},{"subitem_text_language":"en","subitem_text_value":"Institute of Space and Aeronautical Science"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"谷田, 好通"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"斎藤, 喜夫"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"TANIDA, Yoshimichi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"SAITO, Yoshio","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":"SA0125254.pdf","filesize":[{"value":"2.0 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"SA0125254.pdf","url":"https://jaxa.repo.nii.ac.jp/record/32132/files/SA0125254.pdf"},"version_id":"e8001708-504f-466b-9642-3758686d5262"}]},"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":"departmental bulletin paper","resourceuri":"http://purl.org/coar/resource_type/c_6501"}]},"item_title":"平行側壁をもつ後退翼に関する実験的研究","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"平行側壁をもつ後退翼に関する実験的研究"}]},"item_type_id":"9","owner":"1","path":["1890","1910"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"32132","relation_version_is_last":true,"title":["平行側壁をもつ後退翼に関する実験的研究"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-21T00:40:10.901508+00:00"}