{"created":"2023-06-20T15:15:00.773410+00:00","id":45046,"links":{},"metadata":{"_buckets":{"deposit":"1d59d71a-f960-4405-b620-3db6d162b4e8"},"_deposit":{"created_by":1,"id":"45046","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"45046"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00045046","sets":["1887:1893","1896:1898:1913:1917"]},"author_link":["472634","472635","472637","472636","472632","472633"],"item_3_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Wind tunnel Investigation of the Rolling moment of a Rectangular Wing with some Winglets on the Left Upper Tip"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1983-11","bibliographicIssueDateType":"Issued"},"bibliographicPageStart":"28","bibliographicVolumeNumber":"788","bibliographic_titles":[{"bibliographic_title":"航空宇宙技術研究所報告"},{"bibliographic_title":"Technical Report of National Aerospace Laboratory TR-788","bibliographic_titleLang":"en"}]}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"Wind tunnel tests were conducted to investigate the increment of rolling moment due to winglet mounted on the left upper tip of a rectangular wing of aspect ratio of 5.2 with a NACA 0012 section. Two planforms of winglets, rectangular and swept back forms, were tested. Both winglets are equipped with plain flaps to control their side forces. The winglets were canted outboard 90deg or 75deg dihedral and toed in or out up to 20deg relative to the wind chord. The flaps of the winglets were also deflected up to ±30deg. The low speed(Reynold’s number based on wing chord 5×10(exp 5))data were obtained over angles of attack of approximately ±15deg and at the angles of side slip of 0deg and ±10deg. The results indicated that a single winglet produce a relatively large rolling moment with side force, but when left upper and right lower winglets were combined at a time the two rolling moments canceled each other out. It was also found that the incremental rolling moment by a single winglet of 75deg dihedral is about 40％ larger than that of 90deg dihedral. For winglets with the same dihedral, the effect of winglet planform on the incremental rolling moment appeared to be not so large as expected. In order to find the acting centers of the incremental lift and the side force due to winglets, a simple formula is proposed to relate the incremental rolling moment by winglets with those two forces. Experimental data show that the incremental lift center over the wing may be considered to be in the neighborhood of 60％ wing spanwise station if the side force center of the winglet is assumed to be at the centroid. Deviations of the center of both forces are though to be ±8％ of wing semispan and ±5％ of winglet semispan respectively.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: NALTR0788000","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 TR-788","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":"0389-4010","subitem_source_identifier_type":"ISSN"}]},"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新型航空機研究グループ"},{"subitem_text_value":"航空宇宙技術研究所新型航空機研究グループ"},{"subitem_text_value":"航空宇宙技術研究所新型航空機研究グループ"}]},"item_3_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"V/STOL Aircraft Research Group, National Aerospace Laboratory(NAL)"},{"subitem_text_language":"en","subitem_text_value":"V/STOL Aircraft Research Group, National Aerospace Laboratory(NAL)"},{"subitem_text_language":"en","subitem_text_value":"V/STOL Aircraft Research Group, National Aerospace Laboratory(NAL)"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"岩崎, 昭人"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"滝澤, 直人"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"川幡, 長勝"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"IWASAKI, Akihito","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"TAKIZAWA, NAOTO","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"KAWAHATA, Nagakatsu","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":"2020-01-29"}],"displaytype":"detail","filename":"naltr00788.pdf","filesize":[{"value":"2.6 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"naltr00788.pdf","url":"https://jaxa.repo.nii.ac.jp/record/45046/files/naltr00788.pdf"},"version_id":"e784be52-9bb9-4c30-8845-ccb486632e40"}]},"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":"片側翼端小翼付矩形翼の横揺れモーメント 低速風胴実験","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"片側翼端小翼付矩形翼の横揺れモーメント 低速風胴実験"}]},"item_type_id":"3","owner":"1","path":["1893","1917"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"45046","relation_version_is_last":true,"title":["片側翼端小翼付矩形翼の横揺れモーメント 低速風胴実験"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T21:46:14.687972+00:00"}