{"created":"2023-06-20T15:07:46.797935+00:00","id":37142,"links":{},"metadata":{"_buckets":{"deposit":"7a6615c5-97bb-41ab-b312-ac14bef03b1f"},"_deposit":{"created_by":1,"id":"37142","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"37142"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00037142","sets":["1887:1891","1896:1898:1913:1915"]},"author_link":["479119","479118"],"item_5_alternative_title_1":{"attribute_name":"その他のタイトル","attribute_value_mlt":[{"subitem_alternative_title":"アロー翼形態に関する遷音速フラッタ特性の研究"}]},"item_5_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1998-02","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"107","bibliographicPageStart":"99","bibliographicVolumeNumber":"37","bibliographic_titles":[{"bibliographic_title":"航空宇宙技術研究所特別資料"},{"bibliographic_title":"Special Publication of National Aerospace Laboratory","bibliographic_titleLang":"en"}]}]},"item_5_description_14":{"attribute_name":"会議概要（会議名, 開催地, 会期, 主催者等）","attribute_value_mlt":[{"subitem_description":"航空宇宙技術研究所 12-13 Jun. 1997 東京 日本","subitem_description_type":"Other"}]},"item_5_description_15":{"attribute_name":"会議概要（会議名, 開催地, 会期, 主催者等）（英）","attribute_value_mlt":[{"subitem_description":"National Aerospace Laboratory 12-13 Jun. 1997 Tokyo Japan","subitem_description_type":"Other"}]},"item_5_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"非定常空力ツールとして、通常のDLM(ダブレット格子法)コードに加えて、フルポテンシャルコード(USTF3)を用いて、超音速輸送機の典型的なアロー翼形態に関する遷音速フラッタ特性を研究した。DLMコードを用いた解析では、マッハ数0.95までは、剛性設計モデルの対称モードフラッタ(燃料満載条件時)は、逆対称モードフラッタよりも常にクリティカルで、一方、USTF3を用いた解析では、逆対称モードフラッタは遷音速ディップ現象によりマッハ1近傍で極小フラッタ速度をとり、マッハ数0.90以上では、対称モードフラッタよりもクリティカルになった。また、逆対称モードフラッタと対照的に、対称モードフラッタでは遷音速ディップ現象が起きないことも示した。","subitem_description_type":"Abstract"}]},"item_5_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"Transonic flutter characteristics of a typical arrow wing configuration of a supersonic transport have been studied by using the full potential code (USTF3) in addition to the usual DLM (Doublet Lattice Method) code as the unsteady aerodynamic tools. According to the analyzes using the DLM code, the symmetric mode flutter (for full fuel condition) of the stiffness designed model is always more critical than the anti-symmetric mode flutter for Mach numbers up to 0.95, while the analyzes by using the USTF3 say that the anti-symmetric mode flutter becomes more critical than the symmetric mode flutter for Mach numbers greater than 0.90 taking the minimum flutter velocity around Mach one due to the transonic dip phenomenon. It also has been shown that the symmetric mode flutter does not show the transonic-dip phenomenon in contrast to the anti-symmetric mode flutter.","subitem_description_type":"Other"}]},"item_5_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0001433016","subitem_description_type":"Other"}]},"item_5_description_33":{"attribute_name":"レポート番号","attribute_value_mlt":[{"subitem_description":"レポート番号: NAL SP-37","subitem_description_type":"Other"}]},"item_5_publisher_8":{"attribute_name":"出版者","attribute_value_mlt":[{"subitem_publisher":"航空宇宙技術研究所"}]},"item_5_publisher_9":{"attribute_name":"出版者（英）","attribute_value_mlt":[{"subitem_publisher":"National Aerospace Laboratory (NAL)"}]},"item_5_source_id_21":{"attribute_name":"ISSN","attribute_value_mlt":[{"subitem_source_identifier":"0289-260X","subitem_source_identifier_type":"ISSN"}]},"item_5_source_id_24":{"attribute_name":"書誌レコードID","attribute_value_mlt":[{"subitem_source_identifier":"AN10097345","subitem_source_identifier_type":"NCID"}]},"item_5_text_6":{"attribute_name":"著者所属","attribute_value_mlt":[{"subitem_text_value":"九州大学 工学部　航空工学科"}]},"item_5_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"Kyushu University Department of Aeronautics and Astronautics, Faculty of Engineering"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"磯貝, 紘二"}],"nameIdentifiers":[{"nameIdentifier":"479118","nameIdentifierScheme":"WEKO"}]},{"creatorNames":[{"creatorName":"Isogai, Koji","creatorNameLang":"en"}],"nameIdentifiers":[{"nameIdentifier":"479119","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":"2020-02-10"}],"displaytype":"detail","filename":"nalsp0037016.pdf","filesize":[{"value":"1.2 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"nalsp0037016.pdf","url":"https://jaxa.repo.nii.ac.jp/record/37142/files/nalsp0037016.pdf"},"version_id":"82aab9fd-b45a-487b-a117-d0940179603b"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"超音速輸送機","subitem_subject_scheme":"Other"},{"subitem_subject":"アロー翼","subitem_subject_scheme":"Other"},{"subitem_subject":"遷音速フラッタ","subitem_subject_scheme":"Other"},{"subitem_subject":"非定常空力特性","subitem_subject_scheme":"Other"},{"subitem_subject":"空力解析ツール","subitem_subject_scheme":"Other"},{"subitem_subject":"ダブレット格子法","subitem_subject_scheme":"Other"},{"subitem_subject":"DLMコード","subitem_subject_scheme":"Other"},{"subitem_subject":"フルポテンシャルコード","subitem_subject_scheme":"Other"},{"subitem_subject":"剛性モデル","subitem_subject_scheme":"Other"},{"subitem_subject":"対称モードフラッタ","subitem_subject_scheme":"Other"},{"subitem_subject":"遷音速ディップ現象","subitem_subject_scheme":"Other"},{"subitem_subject":"逆対称モードフラッタ","subitem_subject_scheme":"Other"},{"subitem_subject":"フラッタ限界速度","subitem_subject_scheme":"Other"},{"subitem_subject":"マッハ数依存不安定現象","subitem_subject_scheme":"Other"},{"subitem_subject":"supersonic transport","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"arrow wing","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"transonic flutter","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"unsteady aerodynamic characteristics","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"aerodynamic analysis tool","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"doublet lattice method","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"DLM code","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"full potential code","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"stiffness model","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"symmetric mode flutter","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"transonic dip phenomenon","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"antisymmetric mode flutter","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"flutter critical velocity","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"Mach number dependent critical phenomenon","subitem_subject_language":"en","subitem_subject_scheme":"Other"}]},"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":"conference paper","resourceuri":"http://purl.org/coar/resource_type/c_5794"}]},"item_title":"Study on transonic flutter characteristics of an arrow wing configuration","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"Study on transonic flutter characteristics of an arrow wing configuration","subitem_title_language":"en"}]},"item_type_id":"5","owner":"1","path":["1891","1915"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"37142","relation_version_is_last":true,"title":["Study on transonic flutter characteristics of an arrow wing configuration"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T21:25:01.654325+00:00"}