{"created":"2023-06-20T15:14:57.866805+00:00","id":44983,"links":{},"metadata":{"_buckets":{"deposit":"28a6d30d-838f-433a-a889-feefd782116d"},"_deposit":{"created_by":1,"id":"44983","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"44983"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00044983","sets":["1887:1893","1896:1898:1913:1917"]},"author_link":["472351","472348","472350","472349"],"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1982-08","bibliographicIssueDateType":"Issued"},"bibliographicPageStart":"33","bibliographicVolumeNumber":"726T","bibliographic_titles":[{},{"bibliographic_title":"Technical Report of National Aerospace Laboratory TR-726T","bibliographic_titleLang":"en"}]}]},"item_3_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"超臨界翼型を持つ3次元後退翼の遷音速領域におけるフラッタ特性を,衝撃波を考慮した非定常3次元空気力を用いた数値シミュレーションによって予測し,NASAで行われた実験結果と比較した。数値シミュレーションの手法としては,流れの場を支配する方程式(完全ポテンシャル方程式)と翼の運動方程式を連立させて,時間の進行に従って解き,翼の弾性変形の応答を直接的に求める方法を用いている。後退翼の特徴であるフラッタ限界値の遷音速における落ち込み現象が,数値シミュレーションによって予測されたが,落ち込みの起こるマッハ数は実験値よりも約0.05低めであった。このことを除けば,数値シミュレーションによって予測された,フラッタ発生動圧,フラッタ振動数等は実験値と比較的良い一致を示した。また,本報告では,遷音速流れ中で振動している超臨界翼に作用する非定常空気力の振舞いも詳細に検討されている。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"The time marching three-dimensional unsteady transonic full potential code USTF3 is applied to the prediction of the flutter boundary of a supercritical wing for which reliable experimental data exist. The governing flow equation and the structural equations are integrated simultaneously to obtain the time dependent aeroelastic response of the wing. The transonic dip of the flutter boundary is predicted by the present calculations but at about 0.05 Mach number lower than that of the experiment. Expect this, the flutter dynamic pressures and the flutter frequencies predicted by the present calculations show close agreement with those observed in the experiment. THe behavior of the unsteady pressure distributions on the supercritical wing oscillating in pitch are also examined in detail.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: NALTR0726000","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-726T","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機体第一部"},{"subitem_text_value":"ファコム・ハイタック株式会社"}]},"item_3_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"First Airframe Division, National Aerospace Laboratory(NAL)"},{"subitem_text_language":"en","subitem_text_value":"FACOM-HITACH Inc."}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"磯貝, 紘二"}],"nameIdentifiers":[{"nameIdentifier":"472348","nameIdentifierScheme":"WEKO"}]},{"creatorNames":[{"creatorName":"末次, 公平"}],"nameIdentifiers":[{"nameIdentifier":"472349","nameIdentifierScheme":"WEKO"}]},{"creatorNames":[{"creatorName":"ISOGAI, Koji","creatorNameLang":"en"}],"nameIdentifiers":[{"nameIdentifier":"472350","nameIdentifierScheme":"WEKO"}]},{"creatorNames":[{"creatorName":"SUETSUGU, Kohei","creatorNameLang":"en"}],"nameIdentifiers":[{"nameIdentifier":"472351","nameIdentifierScheme":"WEKO"}]}]},"item_files":{"attribute_name":"ファイル情報","attribute_type":"file","attribute_value_mlt":[{"accessrole":"open_date","date":[{"dateType":"Available","dateValue":"2020-01-29"}],"displaytype":"detail","filename":"naltr0726t.pdf","filesize":[{"value":"1.9 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"naltr0726t.pdf","url":"https://jaxa.repo.nii.ac.jp/record/44983/files/naltr0726t.pdf"},"version_id":"4d62b896-1cfe-4d98-9713-748a0836216d"}]},"item_language":{"attribute_name":"言語","attribute_value_mlt":[{"subitem_language":"eng"}]},"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":"Numerical Simulation of Transonic Flutter of a Supercritical Wing","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"Numerical Simulation of Transonic Flutter of a Supercritical Wing","subitem_title_language":"en"}]},"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":"44983","relation_version_is_last":true,"title":["Numerical Simulation of Transonic Flutter of a Supercritical Wing"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T21:47:23.961217+00:00"}