{"created":"2023-06-20T15:07:57.911854+00:00","id":37342,"links":{},"metadata":{"_buckets":{"deposit":"11830613-1252-4385-855a-419aa214578e"},"_deposit":{"created_by":1,"id":"37342","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"37342"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00037342","sets":["1887:1891","1896:1898:1913:1915"]},"author_link":["480247","480243","480242","480246","480241","480245","480240","480244"],"item_5_alternative_title_1":{"attribute_name":"その他のタイトル","attribute_value_mlt":[{"subitem_alternative_title":"逆問題解法を用いたNAL-SSTの主翼設計"}]},"item_5_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1999-02","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"196","bibliographicPageStart":"191","bibliographicVolumeNumber":"41","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 24-26 Jun. 1998 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 24-26 Jun. 1998 Tokyo Japan","subitem_description_type":"Other"}]},"item_5_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"超音速逆設計法を使ってNAL-SST(超音速輸送機)の主翼の空力形状を設計した。この方法はSSTの主翼-胴体配置を取扱い、各スパン毎の主翼断面形状をもたらす。この設計システムは新しい逆問題ソルバとナビエ・ストークスシミュレーションからなっている。設計手順は繰り返し型である。ベースラインの形状は逆問題ソルバのプロセスとして逐次的に補正され、設計された翼によって与えられる圧力分布が目的のものに収束するまでナビエ・ストークスシミュレーションが繰り返される。設計目標とする主翼-胴体配置は、M(sub infinity)=2.0における自然層流(NLF)翼である。この方法によって、より良い翼形状が設計された。それは従来の線形理論によるものよりも望ましい特性を備えている。","subitem_description_type":"Abstract"}]},"item_5_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"The aerodynamic shape of a wing for NAL's SST (Supersonic Transport) has been designed by a supersonic inverse design method. This method handles SST's wing fuselage configurations and provides the wing section geometry at every span. The design system consists of a new inverse problem solver and a Navier-Stokes simulation. The design procedure is iterative; the baseline shape is successively modified as the process of the inverse problem solver and Navier-Stokes simulation is iterated until the pressure distribution given by the designed wing converges to the target one. The design target is a NLF (Natural Laminar Flow) wing for the wing fuselage combination at the speed of M(sub infinity) = 2.0. Several design constraints need to be satisfied. By means of the method, a better wing shape has been designed which has much more desirable characteristics than that by the traditional linear theory.","subitem_description_type":"Other"}]},"item_5_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0001958028","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-41","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":"富士通"},{"subitem_text_value":"航空宇宙技術研究所"},{"subitem_text_value":"東北大学 工学部"},{"subitem_text_value":"東北大学 工学部"}]},"item_5_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"Fujitsu Ltd"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory"},{"subitem_text_language":"en","subitem_text_value":"Tohoku University Faculty of Engineering"},{"subitem_text_language":"en","subitem_text_value":"Tohoku University Faculty of Engineering"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"松島, 紀佐"}],"nameIdentifiers":[{"nameIdentifier":"480240","nameIdentifierScheme":"WEKO"}]},{"creatorNames":[{"creatorName":"岩宮, 敏幸"}],"nameIdentifiers":[{"nameIdentifier":"480241","nameIdentifierScheme":"WEKO"}]},{"creatorNames":[{"creatorName":"Jeong, Sinkyu"}],"nameIdentifiers":[{"nameIdentifier":"480242","nameIdentifierScheme":"WEKO"}]},{"creatorNames":[{"creatorName":"大林, 茂"}],"nameIdentifiers":[{"nameIdentifier":"480243","nameIdentifierScheme":"WEKO"}]},{"creatorNames":[{"creatorName":"Matsushima, Kisa","creatorNameLang":"en"}],"nameIdentifiers":[{"nameIdentifier":"480244","nameIdentifierScheme":"WEKO"}]},{"creatorNames":[{"creatorName":"Iwamiya, Toshiyuki","creatorNameLang":"en"}],"nameIdentifiers":[{"nameIdentifier":"480245","nameIdentifierScheme":"WEKO"}]},{"creatorNames":[{"creatorName":"Jeong, Sinkyu","creatorNameLang":"en"}],"nameIdentifiers":[{"nameIdentifier":"480246","nameIdentifierScheme":"WEKO"}]},{"creatorNames":[{"creatorName":"Obayashi, Shigeru","creatorNameLang":"en"}],"nameIdentifiers":[{"nameIdentifier":"480247","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":"nalsp0041028.pdf","filesize":[{"value":"510.1 kB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"nalsp0041028.pdf","url":"https://jaxa.repo.nii.ac.jp/record/37342/files/nalsp0041028.pdf"},"version_id":"da4e4267-e011-4ff1-b014-aa0dda97d0f7"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"逆問題","subitem_subject_scheme":"Other"},{"subitem_subject":"空力形状","subitem_subject_scheme":"Other"},{"subitem_subject":"主翼","subitem_subject_scheme":"Other"},{"subitem_subject":"断面形状","subitem_subject_scheme":"Other"},{"subitem_subject":"ナビエ・ストークス・シミュレーション","subitem_subject_scheme":"Other"},{"subitem_subject":"線形理論","subitem_subject_scheme":"Other"},{"subitem_subject":"圧力分布","subitem_subject_scheme":"Other"},{"subitem_subject":"繰り返し型","subitem_subject_scheme":"Other"},{"subitem_subject":"流れ場","subitem_subject_scheme":"Other"},{"subitem_subject":"ベルヌーイ定理","subitem_subject_scheme":"Other"},{"subitem_subject":"摂動速度ポテンシャル","subitem_subject_scheme":"Other"},{"subitem_subject":"NLF","subitem_subject_scheme":"Other"},{"subitem_subject":"自然層流","subitem_subject_scheme":"Other"},{"subitem_subject":"SST","subitem_subject_scheme":"Other"},{"subitem_subject":"超音速輸送機","subitem_subject_scheme":"Other"},{"subitem_subject":"inverse problem","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"aerodynamic shape","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"wing","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"section geometry","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"Navier Stokes simulation","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"linear theory","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"pressure distribution","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"iterative type","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"flow field","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"Bernoulli's theorem","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"perturbation velocity potential","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"NLF","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"natural laminar flow","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"SST","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"supersonic transport","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":"Aerodynamic shape design of a wing for NAL's SST using an inverse problem","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"Aerodynamic shape design of a wing for NAL's SST using an inverse problem","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":"37342","relation_version_is_last":true,"title":["Aerodynamic shape design of a wing for NAL's SST using an inverse problem"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T21:21:27.987523+00:00"}