{"created":"2023-06-20T15:12:58.779827+00:00","id":42864,"links":{},"metadata":{"_buckets":{"deposit":"80045434-d397-4667-a1c5-e7326a04cbd2"},"_deposit":{"created_by":1,"id":"42864","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"42864"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00042864","sets":["1887:1893","1896:1898:1913:1917"]},"author_link":["460858","460857","460849","460851","460852","460853","460854","460856","460850","460855"],"item_3_alternative_title_1":{"attribute_name":"その他のタイトル","attribute_value_mlt":[{"subitem_alternative_title":"遷音速領域での外翼前縁フラップによる揚抗比改善について"}]},"item_3_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Lift to drag ratio improvement by leading-edge flap at transonic regions"},{"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":"1459","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":"クランクト・アロー翼を有する超音速航空機(SST: Supersonic Transport)形態では外翼側の後退角を浅くしアスペクト比をより大きくすることで低速空力性能が向上される。そのため後退角の浅い外翼前縁では、設計マッハ数において超音速前縁となり、鋭い前縁形状を有する。しかし、外翼前縁部が亜音速前縁となる遷音速領域では、外翼の鋭い前縁で流れが剥離しやすく、これにより空力性能の低下が懸念される。本研究では超音速前縁形状を有するSST形態の外翼前縁部をフラップ化し、操舵することにより遷音速領域での外翼前縁フラップによる揚抗比の向上に対する有効性を風洞実験により明らかにした。外翼前縁フラップを操舵してない基本形態とフラップ舵角を5度、12.2度に操舵させた場合で空気力、翼表面静圧の比較を行った。本実験範囲内では比較的に高い揚力の範囲では外翼フラップ操舵により抵抗が低減され、揚抗比が向上されることを確認した。このような抵抗の低減はフラップ操舵により前縁で流れの剥離を抑え、剥離渦の発生を抑制させることが主要因であった。今回の実験結果をもとにして揚力係数を一定値に保ったときに揚抗比を最大にする最適フラップ舵角を求め、これらの特性について考察を行った。本研究で得られた知見により、今後、遷音速領域における最適フラップ形状の設計に研究を進める。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"Wind tunnel tests were conducted to investigate lift to drag ratio improvement by the leading-edge flap of the outer wing on an SST model at transonic regions. Force measurements and surface pressure measurements were performed for the SST model with and without outer leading-edge flaps of 5 and 12.2 deg deflection angles. The lift to drag ratio was improved due to a reduction in the drag component, because the flow was attached to the leading edge surface of the wing. The optimum flap deflection angles to attain the maximum lift to drag ratio at a fixed lift coefficient were estimated using experimental results.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0046108000","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-1459","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":"1347-4588","subitem_source_identifier_type":"ISSN"}]},"item_3_source_id_24":{"attribute_name":"書誌レコードID","attribute_value_mlt":[{"subitem_source_identifier":"AN00311347","subitem_source_identifier_type":"NCID"}]},"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 次世代超音速機プロジェクトセンター"},{"subitem_text_value":"東京大学 大学院"},{"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"},{"subitem_text_value":"東京大学 大学院工学系研究科"}]},"item_3_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Next Generation SST Project Center"},{"subitem_text_language":"en","subitem_text_value":"University of Tokyo Graduate School"},{"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"},{"subitem_text_language":"en","subitem_text_value":"University of Tokyo Graduate School of Engineering"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"Kwak, Dong-Youn"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"宮田, 勝弘"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"野口, 正芳"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"吉田, 憲司"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"李家, 賢一"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Kwak, Dong-Youn","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Miyata, Katsuhiro","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Noguchi, Masayoshi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Yoshida, Kenji","creatorNameLang":"en"}],"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":"2020-01-28"}],"displaytype":"detail","filename":"naltr0001459.pdf","filesize":[{"value":"1.0 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"naltr0001459.pdf","url":"https://jaxa.repo.nii.ac.jp/record/42864/files/naltr0001459.pdf"},"version_id":"ff1ab1e9-80da-42da-b8ad-baca6ae489eb"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"SST","subitem_subject_scheme":"Other"},{"subitem_subject":"遷音速風洞試験","subitem_subject_scheme":"Other"},{"subitem_subject":"L/D比","subitem_subject_scheme":"Other"},{"subitem_subject":"前縁フラップ","subitem_subject_scheme":"Other"},{"subitem_subject":"仰角","subitem_subject_scheme":"Other"},{"subitem_subject":"空力","subitem_subject_scheme":"Other"},{"subitem_subject":"空力係数","subitem_subject_scheme":"Other"},{"subitem_subject":"モデル","subitem_subject_scheme":"Other"},{"subitem_subject":"高揚力装置","subitem_subject_scheme":"Other"},{"subitem_subject":"研究開発","subitem_subject_scheme":"Other"},{"subitem_subject":"面圧測定","subitem_subject_scheme":"Other"},{"subitem_subject":"偏向角","subitem_subject_scheme":"Other"},{"subitem_subject":"SST","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"transonic wind tunnel test","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"L/D ratio","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"leading edge flap","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"angle of attack","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"aerodynamic force","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"aerodynamic coefficient","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"model","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"high lift device","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"research and development","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"surface pressure measurement","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"deflection angle","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":"42864","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":"2023-06-20T22:22:59.641806+00:00"}