{"created":"2023-06-20T15:11:32.423957+00:00","id":41222,"links":{},"metadata":{"_buckets":{"deposit":"2aebc43e-7cc8-4487-b8e8-cdb3b685b68d"},"_deposit":{"created_by":1,"id":"41222","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"41222"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00041222","sets":["1887:1893","1896:1898:1913:1917"]},"author_link":["451266","451271","451267","451273","451269","451272","451268","451270"],"item_3_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Low speed aerodynamic characteristics of delta wings with vortex flaps: 60 deg and 70 deg Delta wings"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1994-07","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"13","bibliographicPageStart":"1","bibliographicVolumeNumber":"1245","bibliographic_titles":[{"bibliographic_title":"航空宇宙技術研究所報告"},{"bibliographic_title":"Technical Report of National Aerospace Laboratory","bibliographic_titleLang":"en"}]}]},"item_3_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"ボルテックス･フラップ付きデルタ翼の後退角の変化が空力特性に及ぼす影響を調べるために、後退角70度のボルテックス･フラップ付きデルタ翼模型を用いて風洞実験を行った。空気力、表面圧力測定とオイルフロー法による流れの可視化を行った。得られた結果と既に実施した後退角60度模型の実験結果との比較を行った。その結果、70度デルタ翼においてもボルテックス･フラップの効果は確認されたが、60度デルタ翼の場合よりも狭い揚力係数範囲内で揚抗比の向上は達成された。また、最大の揚抗比向上を達成するフラップ形態において、60度デルタ翼とは異なるフラップ周りの流れパターンが70度デルタ翼において観察された。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"Low-speed wind tunnel tests have been made on a 70 deg delta wing model with tapered vortex flaps to investigate the effects of the sweep-back angle on the performance of vortex flaps. The force, surface pressure measurements and oil flow visualization tests were made on a 0.5 m span 70 deg delta wing model. The results were compared between 60 deg and 70 deg delta wing models. Flow patterns around the vortex flaps at the optimum lift/drag ratio flap configuration of 70 deg delta wing were found to be different from those of 60 deg delta wing. The maximum lift/drag ratio improvement for 70 deg delta wing is attained when a separated region is formed over the whole vortex flap surface.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0004253000","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-1245","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"},{"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":"National Aerospace Laboratory Advanced Aircraft Research Group"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Advanced Aircraft Research Group"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Advanced Aircraft Research Group"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Advanced Aircraft Research Group"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"李家, 賢一"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"藤田, 敏美"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"岩崎, 昭人"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"藤枝, 郭俊"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Rinoie, Kenichi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Fujita, Toshimi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Iwasaki, Akihito","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Fujieda, Hirotoshi","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":"naltr01245.pdf","filesize":[{"value":"1.5 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"naltr01245.pdf","url":"https://jaxa.repo.nii.ac.jp/record/41222/files/naltr01245.pdf"},"version_id":"cd01ebed-cee5-42e0-b0dd-cb7363f9a366"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"ボルテックスフラップ","subitem_subject_scheme":"Other"},{"subitem_subject":"デルタ翼空気力学","subitem_subject_scheme":"Other"},{"subitem_subject":"デルタ翼低速特性","subitem_subject_scheme":"Other"},{"subitem_subject":"前縁剥離渦","subitem_subject_scheme":"Other"},{"subitem_subject":"低速風洞試験","subitem_subject_scheme":"Other"},{"subitem_subject":"表面圧力計測","subitem_subject_scheme":"Other"},{"subitem_subject":"オイルフロー可視化","subitem_subject_scheme":"Other"},{"subitem_subject":"デルタ翼揚抗比","subitem_subject_scheme":"Other"},{"subitem_subject":"後退翼効果","subitem_subject_scheme":"Other"},{"subitem_subject":"超音速翼形状","subitem_subject_scheme":"Other"},{"subitem_subject":"前縁デバイス","subitem_subject_scheme":"Other"},{"subitem_subject":"高迎角空気力学","subitem_subject_scheme":"Other"},{"subitem_subject":"vortex flap","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"delta wing aerodynamics","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"low speed delta wing characteristic","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"leading edge separation vortex","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"low speed wind tunnel test","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"surface pressure measurement","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"oil flow visualization","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"delta wing lift to drag ratio","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"sweepback angle effect","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"supersonic wing configuration","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"leading edge device","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"high angle of attack aerodynamics","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":"ボルテックス･フラップ付きデルタ翼の低速空力特性について:後退角60度と70度の比較","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"ボルテックス･フラップ付きデルタ翼の低速空力特性について:後退角60度と70度の比較"}]},"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":"41222","relation_version_is_last":true,"title":["ボルテックス･フラップ付きデルタ翼の低速空力特性について:後退角60度と70度の比較"],"weko_creator_id":"1","weko_shared_id":1},"updated":"2023-06-20T19:11:49.082158+00:00"}