{"created":"2023-06-20T14:36:03.151963+00:00","id":2350,"links":{},"metadata":{"_buckets":{"deposit":"5b7bd07d-8863-42e6-83f9-b33373dbd496"},"_deposit":{"created_by":1,"id":"2350","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"2350"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00002350","sets":["1887:1893","9:10:309:339"]},"author_link":["5565","5564","5563","5568","5567","5562","5570","5566","5571","5569"],"item_3_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Experimental research of rolling moment characteristics on an SST configuration at high incidence angles"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"2005-03-15","bibliographicIssueDateType":"Issued"},"bibliographicVolumeNumber":"JAXA-RR-04-028","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":"風洞実験を行い、SST形態の低速高迎角ロール特性について調べた。模型のピッチ角を固定しロール方向に静的な運動を与え、空気力や翼表面静圧を計測した。また、前縁剥離渦の挙動を調べるためステレオPIV計測システムを用いて流速分布を計測した。低いピッチ角では線形的で安定なローリングモーメントが働くが、ピッチ角が増加するにつれ大きなロール角付近で非線形的なロール特性が見られた。特にピッチ角20度では小さいロール角の範囲ではロールに対して線形的で安定なモーメントが働くが、ロール角15度から25度付近で急激な変化が見られ、これらのロール角では不安定なローリングモーメントが働く。このピッチ角20度で見られた急激な不安定ローリングモーメントは翼表面静圧分布によると83％コード位置付近の流れが強く関係している。ロールにより下降した翼側のサクション・ピークの低下と上昇した翼側のサクション・ピークの増大が急激に不安定ローリングモーメントを増加させる方に寄与している。PIVによる流速分布計測結果によると、ピッチ角20度、83％コード位置で見られた不安定なローリングモーメントは内翼渦の崩壊(vortex breakdown)が強く関連している。ロール角0度の場合に比べ、ロールにより下降した翼側では渦崩壊位置は翼頂点に向かって前進し、これにより渦吸引力は減少し、逆にロールにより上昇する翼側では渦崩壊位置は後退し、渦吸引力は増加する。これらの渦崩壊位置の変化は不安定なローリングモーメントを発生させる。更には、下降した翼側のサクションの減少より上昇した翼側のサクションの増加が大きく、これにより機首下げピッチングモーメントの増加が発生している。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"Wind tunnel tests were performed to investigate rolling moment characteristics of a cranked arrow wing SST configuration at high incidence angles. Force measurements and surface static pressure measurements were conducted with the model rolled statically. In order to understand behaviors of the leading edge separation vortex, stereoscopic PIV survey was performed at x/C(sub r) = 0.55 and x/C(sub r) = 0.83. With increasing roll angles, linearly stable rolling moments were obtained at low incidence angles, while abrupt changes from stable to unstable rolling moments were obtained at incidence angle of 20 degrees. Abrupt change of the rolling moment was strongly related to sudden increments of nose down pitching moments. Variations of suction peaks on pressure distributions at x/C(sub r) = 0.83 contribute to unstable rolling moment component. These variations of suction peaks that induce unstable rolling moment are related to the vortex breakdown characteristics. The asymmetry of the chordwise locations of the inboard vortex breakdown on windward and leeward wings induces the sudden change of rolling moments. Because of the effects due to retreating of the vortex breakdown on the leeward wing are larger than those due to moving forward of the vortex breakdown location on the windward wing, sudden increment of the nose down pitching moments was obtained.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0048137000","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-04-028","subitem_description_type":"Other"}]},"item_3_publisher_8":{"attribute_name":"出版者","attribute_value_mlt":[{"subitem_publisher":"宇宙航空研究開発機構"}]},"item_3_publisher_9":{"attribute_name":"出版者（英）","attribute_value_mlt":[{"subitem_publisher":"Japan Aerospace Exploration Agency (JAXA)"}]},"item_3_source_id_21":{"attribute_name":"ISSN","attribute_value_mlt":[{"subitem_source_identifier":"1349-1113","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":"AA1192675X","subitem_source_identifier_type":"NCID"}]},"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 総合技術研究本部"},{"subitem_text_value":"東京大学 大学院"},{"subitem_text_value":"宇宙航空研究開発機構 総合技術研究本部"},{"subitem_text_value":"東京大学 大学院工学系研究科"},{"subitem_text_value":"宇宙航空研究開発機構 総合技術研究本部　風洞技術開発センター"}]},"item_3_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics"},{"subitem_text_language":"en","subitem_text_value":"University of Tokyo Graduate School"},{"subitem_text_language":"en","subitem_text_value":"Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics"},{"subitem_text_language":"en","subitem_text_value":"University of Tokyo Graduate School of Engineering"},{"subitem_text_language":"en","subitem_text_value":"Japan Aerospace Exploration Agency Wind Tunnel Technology Center, Institute of Space Technology and Aeronautics"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"Kwak, Dongyoun"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"城武, 雅"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"野口, 正芳"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"李家, 賢一"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"渡辺, 重哉"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Kwak, Dongyoun","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Shirotake, Masashi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Noguchi, Masayoshi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Rinoie, Kenichi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Watanabe, Shigeya","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":"2020-01-15"}],"displaytype":"detail","filename":"48137000.pdf","filesize":[{"value":"3.2 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"48137000.pdf","url":"https://jaxa.repo.nii.ac.jp/record/2350/files/48137000.pdf"},"version_id":"cb8e9b8f-492c-4efd-a0c3-d1df7d53ca29"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"SST","subitem_subject_scheme":"Other"},{"subitem_subject":"ローリングモーメント","subitem_subject_scheme":"Other"},{"subitem_subject":"航空機配置","subitem_subject_scheme":"Other"},{"subitem_subject":"風洞試験","subitem_subject_scheme":"Other"},{"subitem_subject":"圧力測定","subitem_subject_scheme":"Other"},{"subitem_subject":"剥離渦","subitem_subject_scheme":"Other"},{"subitem_subject":"渦崩壊","subitem_subject_scheme":"Other"},{"subitem_subject":"静圧","subitem_subject_scheme":"Other"},{"subitem_subject":"SST","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"rolling moment","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"aircraft configuration","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"wind tunnel test","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"pressure measurement","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"separation vortex","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"vortex breakdown","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"static pressure","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)形態の低速高迎角ロール特性に関する研究","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"超音速航空機(SST)形態の低速高迎角ロール特性に関する研究"}]},"item_type_id":"3","owner":"1","path":["339","1893"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"2350","relation_version_is_last":true,"title":["超音速航空機(SST)形態の低速高迎角ロール特性に関する研究"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-21T09:24:05.993451+00:00"}