{"created":"2021-03-01T07:14:24.816011+00:00","id":35470,"links":{},"metadata":{"_buckets":{"deposit":"c4b20e8b-8769-4980-af6f-1af325b44ddb"},"_deposit":{"id":"35470","owners":[],"pid":{"revision_id":0,"type":"depid","value":"35470"},"status":"published"},"_oai":{"id":"oai:tsukuba.repo.nii.ac.jp:00035470","sets":["2871:2874:834","3:62:5615:3351"]},"item_5_alternative_title_18":{"attribute_name":"その他のタイトル","attribute_value_mlt":[{"subitem_alternative_title":"Transient Vortex Structures of a Discoid Airfoil during Impulsive Incidence Variation"}]},"item_5_biblio_info_6":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"2014-06","bibliographicIssueDateType":"Issued"},"bibliographicIssueNumber":"6","bibliographicPageEnd":"16","bibliographicPageStart":"9","bibliographicVolumeNumber":"34","bibliographic_titles":[{"bibliographic_title":"可視化情報学会論文集"},{"bibliographic_title":"Transactions of the Visualization Society of Japan","bibliographic_titleLang":"en"}]}]},"item_5_creator_3":{"attribute_name":"著者別名","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"Hasegawa, Hiroaki"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Shimakawa, Tatsuya"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Matsuuchi, Kazuo"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Nakagawa, Kenichi"}],"nameIdentifiers":[{}]}]},"item_5_description_4":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"三次元翼として円盤翼を用いて、急激に迎角を変化させた際の過渡的な渦構造をPIV計測により調べた。迎角を0度から定常失速角前の角度および失速角を超える角度まで急激に変化させ、迎角変化速度が揚力特性に及ぼす影響を調べた。特に、迎角変化中の各時刻での渦構造を、各測定面での渦度の等値面を繋ぐことで構築し、揚力変動と渦構造の関連を調べた。定常状態で失速角を超えた流れ場は、翼背面がはく離流れに覆われる。それに対して、急激に迎角を上昇させた場合、定常失速角を超えても失速が抑制され、最大揚力係数が増加した。この傾向は、迎角変化速度が高いほど顕著であった。また、定常失速角を超えた角度まで翼を動かし停止させた場合、急激な揚力低下は起こらず、揚力は定常時の値にゆっくり漸近していく。これは、迎角上昇とともに強くなった翼端渦が、翼停止後の翼背面からの流れの全面はく離を抑制するためである。","subitem_description_type":"Abstract"}]},"item_5_description_5":{"attribute_name":"内容記述","attribute_value_mlt":[{"subitem_description":"  It is necessary to know the unsteady properties determined from the vortex dynamics because the unsteadiness is known to make the force greater. The purpose of this study is to investigate the influence of vortices on transient aerodynamic characteristics of a three-dimensional airfoil whose angle of attack is varied impulsively. In the present experiment, the angle of attack of the airfoil is impulsively changed from 0 deg to the angle set under or beyond the static stall angle. The vortical flow fields were measured by using a stereoscopic PIV technique, and the image of three-dimensional vortex structure was depicted by plotting iso-vorticity surface calculated from the velocity data. The flow separates from the upper surface of the airfoil where the angle of attack increases beyond static stall angle under stationary conditions. On the other hand, when the airfoil is raised to a large angle of attack, high CLmax is attained by changing the rate of an angle of attack with the small non-dimensional rise time T*. The small value of T* indicates fast change in an angle of attack during incidence variation. The tip vortex (TIV) becomes stronger with increasing the angle of attack, and the whole separation on the upper surface of the airfoil is suppressed by the TIV after the airfoil stops. Therefore, CL gradually decreases and the value of CL comes to that of the stationary condition asymptotically.","subitem_description_type":"Other"}]},"item_5_publisher_27":{"attribute_name":"出版者","attribute_value_mlt":[{"subitem_publisher":" 可視化情報学会"}]},"item_5_publisher_28":{"attribute_name":"出版者別名","attribute_value_mlt":[{"subitem_publisher":"The Visualization Society of Japan"}]},"item_5_relation_11":{"attribute_name":"DOI","attribute_value_mlt":[{"subitem_relation_type_id":{"subitem_relation_type_id_text":"10.3154/tvsj.34.9","subitem_relation_type_select":"DOI"}}]},"item_5_select_15":{"attribute_name":"著者版フラグ","attribute_value_mlt":[{"subitem_select_item":"publisher"}]},"item_5_source_id_7":{"attribute_name":"ISSN","attribute_value_mlt":[{"subitem_source_identifier":"1346-5260","subitem_source_identifier_type":"ISSN"}]},"item_5_source_id_9":{"attribute_name":"書誌レコードID","attribute_value_mlt":[{"subitem_source_identifier":"AA12023621","subitem_source_identifier_type":"NCID"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"長谷川, 裕晃"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"島川, 達也"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"松内, 一雄"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"中川, 健一"}],"nameIdentifiers":[{}]}]},"item_files":{"attribute_name":"ファイル情報","attribute_type":"file","attribute_value_mlt":[{"accessrole":"open_date","date":[{"dateType":"Available","dateValue":"2015-09-28"}],"displaytype":"detail","filename":"TVSJ_34-6.pdf","filesize":[{"value":"2.9 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"TVSJ_34-6","url":"https://tsukuba.repo.nii.ac.jp/record/35470/files/TVSJ_34-6.pdf"},"version_id":"2b84b57c-6f53-4c2a-8b51-1e9e1243a985"}]},"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":"journal article","resourceuri":"http://purl.org/coar/resource_type/c_6501"}]},"item_title":"円盤翼の急激迎角変化時の過渡的な渦構造","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"円盤翼の急激迎角変化時の過渡的な渦構造"}]},"item_type_id":"5","owner":"1","path":["834","3351"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-09-28"},"publish_date":"2015-09-28","publish_status":"0","recid":"35470","relation_version_is_last":true,"title":["円盤翼の急激迎角変化時の過渡的な渦構造"],"weko_creator_id":"1","weko_shared_id":5},"updated":"2022-04-27T09:04:24.991016+00:00"}