{"created":"2023-06-20T15:07:30.637867+00:00","id":36877,"links":{},"metadata":{"_buckets":{"deposit":"8137d415-7066-4af9-90a1-c7f3347b9aac"},"_deposit":{"created_by":1,"id":"36877","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"36877"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00036877","sets":["1887:1891","1896:1898:1913:1915"]},"author_link":["477963","477966","477967","477964","477968","477969","477970","477965"],"item_5_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"On an inverse problem for a supersonic airfoils based on Navier-Stokes approximation"}]},"item_5_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1997-01","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"100","bibliographicPageStart":"95","bibliographicVolumeNumber":"34","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 6-7 JUN. 1996 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 6-7 JUN. 1996 Tokyo Japan","subitem_description_type":"Other"}]},"item_5_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"超音速翼型の設計に高梨の反復残差修正法を適用した。翼形状の修正は計算圧した力分布と目標圧力分布の間の圧力残差から計算した逆解法を用いて行った。逆解法はPrandtl-Meyer関数あるいは線形理論により得た。圧力分布はナビエ・ストークス近似が使われているコードNSFOILを使って数値的に得た。幾つかの計算例を紹介した。","subitem_description_type":"Abstract"}]},"item_5_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"Takanashi's iterative residual-correction method is applied to the design of supersonic airfoils. Airfoil geometry correction is obtained by use of inverse solutions calculated from the differences between the computed and the prescribed pressure distributions. Inverse solutions are obtained by Prandtl-Meyer function or linearized theory. The pressure distributions are obtained numerically by the code NSFOIL (Navier-Stokes FOIL), where Navier-Stokes approximations are used. Some examples of the calculations are presented.","subitem_description_type":"Other"}]},"item_5_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0000685018","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-34","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":"名古屋大学 工学部"},{"subitem_text_value":"本田技研工業"},{"subitem_text_value":"航空宇宙技術研究所"},{"subitem_text_value":"航空宇宙技術研究所"}]},"item_5_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"Nagoya University School of Engineering"},{"subitem_text_language":"en","subitem_text_value":"Honda Motor Co Ltd"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"神谷, 信彦"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"玉置, 秀海"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"廣瀬, 直喜"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"石田, 洋治"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Kamiya, Nobuhiko","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Tamaki, Hidemi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Hirose, Naoki","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Ishida, Yoji","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":"2020-02-10"}],"displaytype":"detail","filename":"nalsp0034018.pdf","filesize":[{"value":"513.5 kB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"nalsp0034018.pdf","url":"https://jaxa.repo.nii.ac.jp/record/36877/files/nalsp0034018.pdf"},"version_id":"601058b2-48d9-4a79-976e-ab9b5f351888"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"ナビエ・ストークス近似","subitem_subject_scheme":"Other"},{"subitem_subject":"反復残差修正法","subitem_subject_scheme":"Other"},{"subitem_subject":"逆解法","subitem_subject_scheme":"Other"},{"subitem_subject":"超音速翼","subitem_subject_scheme":"Other"},{"subitem_subject":"表面圧力分布","subitem_subject_scheme":"Other"},{"subitem_subject":"翼幾何学的修正","subitem_subject_scheme":"Other"},{"subitem_subject":"Prandtl-Meyer関数","subitem_subject_scheme":"Other"},{"subitem_subject":"NSFOILコード","subitem_subject_scheme":"Other"},{"subitem_subject":"翼型設計法","subitem_subject_scheme":"Other"},{"subitem_subject":"線形理論","subitem_subject_scheme":"Other"},{"subitem_subject":"高梨法","subitem_subject_scheme":"Other"},{"subitem_subject":"Navier Stokes approximation","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"iterative residual correction method","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"inverse solution","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"supersonic airfoil","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"surface pressure distribution","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"airfoil geometry correction","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"Prandtl Meyer function","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"NSFOIL code","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"airfoil design method","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"linearized theory","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"Takanashi's method","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":"conference paper","resourceuri":"http://purl.org/coar/resource_type/c_5794"}]},"item_title":"ナビアストークス解法をベースにした超音速翼型の逆解法","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"ナビアストークス解法をベースにした超音速翼型の逆解法"}]},"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":"36877","relation_version_is_last":true,"title":["ナビアストークス解法をベースにした超音速翼型の逆解法"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T21:30:01.136710+00:00"}