{"created":"2023-06-20T15:12:58.310846+00:00","id":42855,"links":{},"metadata":{"_buckets":{"deposit":"03bd7dc2-dfca-4ec3-a4b4-0375b5b5ad49"},"_deposit":{"created_by":1,"id":"42855","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"42855"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00042855","sets":["1887:1893","1896:1898:1913:1917"]},"author_link":["460777","460783","460784","460780","460782","460781","460778","460779"],"item_3_alternative_title_1":{"attribute_name":"その他のタイトル","attribute_value_mlt":[{"subitem_alternative_title":"丸い前縁形状の効果"}]},"item_3_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Effects of rounded leading-edges"},{"subitem_alternative_title":"Experimental investigations on high lift devices for an SST"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"2003-05","bibliographicIssueDateType":"Issued"},"bibliographicVolumeNumber":"1456","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":"超音速航空機(SST: Supersonic Transport)機体に内翼前縁ボルテックス・フラップ、外翼前縁フラップ、後縁フラップを適用したときの低速空力特性に対する効果を明らかにするために、クランクトアロー翼を有するSST模型を用いた風洞試験を行い、各種フラップの有効性を検討している。本報では、内翼前縁ボルテックス・フラップの前縁形状を丸くした場合の効果、およびレイノルズ数の違いが丸い前縁ボルテックス・フラップの性能に及ぼす影響について調べた。その結果、前縁を丸くすることにより、揚抗比が最大値をとる揚力係数C(sub L)よりも大きいC(sub L)の範囲(C(sub L)＞0.3)において揚抗比L/Dはわずかに増加することが確認された。また、レイノルズ数が変化した場合の流れ場への影響を調べたところ、オリジナルの前縁形状ではほとんど影響が見られないのに対して、前縁を丸くした形状ではレイノルズ数が増大するにつれてフラップ上に生ずる前縁剥離渦のスパン方向長さが短くなる場合があることが示された。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"The effects of rounded leading-edge vortex flaps were investigated on a cranked arrow wing SST configuration, using wind tunnel measurements. Differences in aerodynamic characteristics were discussed for the non-rounded leading-edge flap-an original design, and for the rounded leading-edge flap. The question of how differences in Reynolds number affects the flow around the rounded leading-edge vortex flaps and the flap performance was also discussed. Some benefit from the lift/drag ratio for the wing with the rounded leading-edge vortex flaps was obtained, as compared with those of the non-rounded vortex flaps at a lift coefficient greater than 0.3. Flow patterns over the rounded leading-edge vortex flaps were observed changing as the Reynolds number increased. The spanwise length of the separated region is reduced as the Reynolds number is increased.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0045943000","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-1456","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"},{"subitem_text_value":"東京大学 大学院工学系研究科"},{"subitem_text_value":"航空宇宙技術研究所 次世代超音速機プロジェクトセンター"},{"subitem_text_value":"航空宇宙技術研究所 次世代超音速機プロジェクトセンター"}]},"item_3_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory"},{"subitem_text_language":"en","subitem_text_value":"University of Tokyo Graduate School of Engineering"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Next Generation SST Project Center"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Next Generation SST Project Center"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"宮田, 勝弘"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"李家, 賢一"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Kwak, Dong-Youn"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"野口, 正芳"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Miyata, Katsuhiro","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Rinoie, Kenichi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Kwak, Dong-Youn","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Noguchi, Masayoshi","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":"2020-01-28"}],"displaytype":"detail","filename":"naltr0001456.pdf","filesize":[{"value":"4.9 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"naltr0001456.pdf","url":"https://jaxa.repo.nii.ac.jp/record/42855/files/naltr0001456.pdf"},"version_id":"859ba96c-26cc-4339-8bec-c801e1264d32"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"SST","subitem_subject_scheme":"Other"},{"subitem_subject":"L/D比","subitem_subject_scheme":"Other"},{"subitem_subject":"丸い前縁","subitem_subject_scheme":"Other"},{"subitem_subject":"高揚力装置","subitem_subject_scheme":"Other"},{"subitem_subject":"翼面圧","subitem_subject_scheme":"Other"},{"subitem_subject":"横流不安定性","subitem_subject_scheme":"Other"},{"subitem_subject":"渦打ち","subitem_subject_scheme":"Other"},{"subitem_subject":"Reynolds数","subitem_subject_scheme":"Other"},{"subitem_subject":"表面粗さ","subitem_subject_scheme":"Other"},{"subitem_subject":"研究開発","subitem_subject_scheme":"Other"},{"subitem_subject":"空力特性","subitem_subject_scheme":"Other"},{"subitem_subject":"空力係数","subitem_subject_scheme":"Other"},{"subitem_subject":"SST","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"L/D ratio","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"rounded leading edge","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"high lift device","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"wing surface pressure distribution","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"cross flow instability","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"vortex flap","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"Reynolds number","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"surface roughness","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"research and development","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"aerodynamic characteristic","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"aerodynamic coefficient","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":"超音速航空機(SST)形態の高揚力装置に関する実験的研究","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"超音速航空機(SST)形態の高揚力装置に関する実験的研究"}]},"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":"42855","relation_version_is_last":true,"title":["超音速航空機(SST)形態の高揚力装置に関する実験的研究"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T22:23:09.333127+00:00"}