{"created":"2023-06-20T14:35:34.249887+00:00","id":1802,"links":{},"metadata":{"_buckets":{"deposit":"caf32a56-4d2d-4921-8d24-334095d50fd1"},"_deposit":{"created_by":1,"id":"1802","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"1802"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00001802","sets":["1887:1893","9:10:25:26"]},"author_link":["475894","475901","475902","475896","475893","475900","475903","475897","475904","475895","475899","475898"],"item_3_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Effect of Vortex Generators on Three-Dimensional Wings in Transonic Flows"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"2018-03-09","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"407","bibliographicPageStart":"1","bibliographicVolumeNumber":"JAXA-RR-17-013","bibliographic_titles":[{"bibliographic_title":"宇宙航空研究開発機構研究開発報告"},{"bibliographic_title":"JAXA Research and Development Report","bibliographic_titleLang":"en"}]}]},"item_3_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"本報告書は, 2011年から2015年にかけJAXAで実施した遷音速バフェット抑制のためのVortex Generator (VG)に関する研究結果をまとめたものである. 既報「遷音速二次元翼に対するVortex Generator効果」の続編にあたる. 既報では, 後退角のない2次元翼に限定し, VGの効果をまとめた. 本報告書では, 実機を模擬した遷音速3次元翼に対するVGの効果をまとめた. 研究は, 風洞実験とComputational Fluid Dynamics(CFD)の双方を用いて行った. 風洞実験においてもCFDにおいても, 航空機形状のNASA Common Research Model (NASA CRM) の主翼を対象とした. VGについては, 矩形形状, かつ, 全てのVGの導入する縦渦の向きが等しいVG列(Co-rotating VGs)を対象とした. 本報告書を実用的な報告書にするという観点から, まず, 本研究から導かれたVGの設計指針とVGの効果に対する仮説を含む原理を示した. その上で, 風洞実験およびCFDにより調べたVGの基本的なパラメータ, 高さ, 長さ, 角度, 間隔のVGの効果に対する感度をそれぞれまとめた. 解析手法については, 風洞実験およびCFDの比較から, 本研究で行ったCFD解析は定性的にはVGの効果を適切に捉えられることが明らかとなった. VGの効果に関する新たな知見を得るために, 既報で調査した後退角のない2次元翼模型と本研究の3次元翼の結果を比較した. さらにCFDにより複数の後退角の無限後退翼について, VGの効果を調べた. その結果, 後退角のある3次元翼においては, VGの導入する縦渦の回転方向が極めて重要であること, VGの前縁が翼端を向くVG 配置 (Toe-Out VGs) が剥離抑制に効果が高いことが明らかとなった. 約30度の後退角をもつNASA CRMの主翼に対してToe-Out VGsを使用する場合は, VGの間隔をVGの高さの80倍としても, VGの効果が明瞭に現れた. この間隔は, 後退角のない2次元翼模型の場合の8倍の間隔である. VGの間隔を広くとれることはVGの設置枚数を減らすことにつながり, VGの巡航時の付加抵抗の低減につながる. 後退角のある3次元翼に対しては, VGの向きをToe-Outに取り, VG の間隔を後退角の大きさを考慮して設計することが極めて重要であることを明らかにした.","subitem_description_type":"Abstract"}]},"item_3_description_18":{"attribute_name":"内容記述","attribute_value_mlt":[{"subitem_description":"形態: カラー図版あり","subitem_description_type":"Other"}]},"item_3_description_19":{"attribute_name":"内容記述（英）","attribute_value_mlt":[{"subitem_description":"Physical characteristics: Original contains color illustrations","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA1730025000","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: JAXA-RR-17-013","subitem_description_type":"Other"}]},"item_3_identifier_registration":{"attribute_name":"ID登録","attribute_value_mlt":[{"subitem_identifier_reg_text":"10.20637/JAXA-RR-17-013/0001","subitem_identifier_reg_type":"JaLC"}]},"item_3_publisher_8":{"attribute_name":"出版者","attribute_value_mlt":[{"subitem_publisher":"宇宙航空研究開発機構(JAXA)"}]},"item_3_publisher_9":{"attribute_name":"出版者（英）","attribute_value_mlt":[{"subitem_publisher":"Japan Aerospace Exploration Agency (JAXA)"}]},"item_3_source_id_22":{"attribute_name":"ISSNONLINE","attribute_value_mlt":[{"subitem_source_identifier":"2433-2216","subitem_source_identifier_type":"ISSN"}]},"item_3_text_6":{"attribute_name":"著者所属","attribute_value_mlt":[{"subitem_text_value":"宇宙航空研究開発機構航空技術部門次世代航空イノベーションハブ(JAXA)"},{"subitem_text_value":"宇宙航空研究開発機構航空技術部門次世代航空イノベーションハブ(JAXA)"},{"subitem_text_value":"宇宙航空研究開発機構航空技術部門次世代航空イノベーションハブ(JAXA)"},{"subitem_text_value":"宇宙航空研究開発機構航空技術部門次世代航空イノベーションハブ(JAXA)"},{"subitem_text_value":"宇宙航空研究開発機構航空技術部門次世代航空イノベーションハブ(JAXA)"},{"subitem_text_value":"宇宙航空研究開発機構航空技術部門FQUROHプロジェクトチーム(JAXA)"}]},"item_3_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"Next Generation Aeronautical Innovation Hub Center, Aeronautical Technology Directorate,Japan Aerospace Exploration Agency (JAXA)"},{"subitem_text_language":"en","subitem_text_value":"Next Generation Aeronautical Innovation Hub Center, Aeronautical Technology Directorate,Japan Aerospace Exploration Agency (JAXA)"},{"subitem_text_language":"en","subitem_text_value":"Next Generation Aeronautical Innovation Hub Center, Aeronautical Technology Directorate,Japan Aerospace Exploration Agency (JAXA)"},{"subitem_text_language":"en","subitem_text_value":"Next Generation Aeronautical Innovation Hub Center, Aeronautical Technology Directorate,Japan Aerospace Exploration Agency (JAXA)"},{"subitem_text_language":"en","subitem_text_value":"Next Generation Aeronautical Innovation Hub Center, Aeronautical Technology Directorate,Japan Aerospace Exploration Agency (JAXA)"},{"subitem_text_language":"en","subitem_text_value":"FQUROH Project Team, Aeronautical Technology Directorate,Japan Aerospace Exploration Agency (JAXA)"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"小池, 俊輔"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"伊藤, 靖"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"楠瀬, 一洋"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"村山, 光宏"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"中北, 和之"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"山本, 一臣"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Koike, Shunsuke","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Ito, Yasushi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Kusunose, Kazuhiro","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Murayama, Mitsuhiro","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Nakakita, Kazuyuki","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Yamamoto, Kazuomi","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":"2020-01-31"}],"displaytype":"detail","filename":"AA1730025000.pdf","filesize":[{"value":"83.9 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"AA1730025000.pdf","url":"https://jaxa.repo.nii.ac.jp/record/1802/files/AA1730025000.pdf"},"version_id":"00d415d4-febf-48f8-9262-34ddfd8b362b"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"Vortex generator","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"Transonic buffet","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"Shock wave boundary layer interaction","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"Streamwise vortex","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"NASA Common Research Model","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":"遷音速三次元翼に対するVortex Generator効果","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"遷音速三次元翼に対するVortex Generator効果"}]},"item_type_id":"3","owner":"1","path":["26","1893"],"pubdate":{"attribute_name":"公開日","attribute_value":"2018-03-12"},"publish_date":"2018-03-12","publish_status":"0","recid":"1802","relation_version_is_last":true,"title":["遷音速三次元翼に対するVortex Generator効果"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T21:38:52.501517+00:00"}