{"created":"2023-06-20T15:15:19.448861+00:00","id":45399,"links":{},"metadata":{"_buckets":{"deposit":"13e57b46-886a-402a-8be7-109b17d34d6c"},"_deposit":{"created_by":1,"id":"45399","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"45399"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00045399","sets":["1887:1893","1896:1898:1913:1917"]},"author_link":["474578","474579"],"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1992-03","bibliographicIssueDateType":"Issued"},"bibliographicPageStart":"16","bibliographicVolumeNumber":"1140T","bibliographic_titles":[{},{"bibliographic_title":"Technical Report of National Aerospace Laboratory TR-1140T","bibliographic_titleLang":"en"}]}]},"item_3_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"前縁ボルテックス・フラップまわりの流れを調べるために低速風洞実験を行った。逆ボルテックス・フラップとボルテックス・プレートの特性も計測した。後退角60度のデルタ翼模型を用いて空気力測定と流れの可視化を行った。その結果,折り曲げたボルテックス・フラップ表面上に大きな前縁剥離渦を形成しない特定の迎角において,デルタ翼の揚抗比が最大になることが示された。またボルテックス・プレートを用いると抗力が減少することが示された。これは翼前方へ働く吸引力が,デルタ翼とボルテックス・プレートとの間の領域に存在するためである。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"Low-speed wind tunnel tests were conducted to investigate the flow around a leading-edge vortex flap at the maximum lift to drag (L/C) condition, and also to measure the performance of an inverted vortex flap and vortex plate. Associated force measurements and flow visualization tests were carried out on a 60 degree delta wing model. Results indicate that the maximum lift to drag ratio for any given flap deflection angle occurs when the flow smoothly comes onto the deflected vortex flap without forming a large leading-edge separation vortex on the flap surface. Use of a vortex plate was found to reduce the drag in comparison to the datum wing, a benefit due to some leading-edge suction acting on the forward facing region between the delta wing and the vortex plate.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: NALTR1140000","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-1140T","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"}]},"item_3_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"Advanced Aircraft Research Group, National Aerospace Laboratory(NAL)"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"李家, 賢一"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"RINOIE, Kenichi","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":"naltr1140t.pdf","filesize":[{"value":"1.5 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"naltr1140t.pdf","url":"https://jaxa.repo.nii.ac.jp/record/45399/files/naltr1140t.pdf"},"version_id":"f1a57a7e-ead4-4bdd-bff1-5cf66cd07e36"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"low-speed aerodynamics;  delta wing;  vortex flap;  votex plate;  leading-edge separation vortex","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":"Experimental Studies of Vortex Flaps and Vortex Plates Part 1. 0.53m Span 60deg Delta Wing","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"Experimental Studies of Vortex Flaps and Vortex Plates Part 1. 0.53m Span 60deg Delta Wing","subitem_title_language":"en"}]},"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":"45399","relation_version_is_last":true,"title":["Experimental Studies of Vortex Flaps and Vortex Plates Part 1. 0.53m Span 60deg Delta Wing"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T21:40:11.612591+00:00"}