{"created":"2023-06-20T15:14:54.889293+00:00","id":44929,"links":{},"metadata":{"_buckets":{"deposit":"c5a350d9-ebae-4953-aea9-ef683bf0274d"},"_deposit":{"created_by":1,"id":"44929","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"44929"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00044929","sets":["1887:1893","1896:1898:1913:1917"]},"author_link":["472008","472003","472006","472005","472007","472004"],"item_3_alternative_title_1":{"attribute_name":"その他のタイトル","attribute_value_mlt":[{"subitem_alternative_title":"完全ポテンシャル流の遷音速翼型設計Ⅰ.数値解法とその適用計算例"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1981-05","bibliographicIssueDateType":"Issued"},"bibliographicPageStart":"44","bibliographicVolumeNumber":"672","bibliographic_titles":[{"bibliographic_title":"航空宇宙技術研究所報告"},{"bibliographic_title":"Technical Report of National Aerospace Laboratory TR-672","bibliographic_titleLang":"en"}]}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"A computational inverse procedure for transonic airfoils, in which geometries are determined from prescribed target pressure distributions, is presented. This is an iterative direct-inverse approach. The following two calculations are iterated until a target pressure distribution coincides with a direct solution on a temporary surface. One is the direct solution, which is calculated using the successive line over-relaxation method which solves the full inviscid compressible potential flow equation in the Neumann problem. The other is a modification of the temporary airfoil geometry, which is determined from the conservation law of mass flux using the normal velocity at the contour, which is obtained by solving the equation in the Dirichlet problem where the target pressure distribution is specified at the temporary contour. Furthermore, a boundary layer calculation is made and a displacement thickness is subtracted to yield an actual airfoil geometry. Several examples illustrating this method are presented for flows with and without shock waves.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: NALTR0672000","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-672","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計算センター"},{"subitem_text_value":"航空宇宙技術研究所空気力学第二部"},{"subitem_text_value":"航空宇宙技術研究所空気力学第二部"}]},"item_3_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"Computer Center, National Aerospace Laboratory(NAL)"},{"subitem_text_language":"en","subitem_text_value":"Second Aerodynamics Division, National Aerospace Laboratory(NAL)"},{"subitem_text_language":"en","subitem_text_value":"Second Aerodynamics Division, National Aerospace Laboratory(NAL)"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"石黒, 登美子"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"神谷, 信彦"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"河合, 伸坦"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"ISHIGURO, Tomiko","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"KAMIYA, Nobuhiko","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"KAWAI, Nobuhiro","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":"2020-01-29"}],"displaytype":"detail","filename":"naltr00672.pdf","filesize":[{"value":"2.7 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"naltr00672.pdf","url":"https://jaxa.repo.nii.ac.jp/record/44929/files/naltr00672.pdf"},"version_id":"f02f0adb-da3c-4f25-b8f0-71f0763cf60f"}]},"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":"Transonic Airfoil Design of Full Potential Flow I.Numerical Procedure and Its Computational Examples","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"Transonic Airfoil Design of Full Potential Flow I.Numerical Procedure and Its Computational Examples","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":"44929","relation_version_is_last":true,"title":["Transonic Airfoil Design of Full Potential Flow I.Numerical Procedure and Its Computational Examples"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T21:48:20.300760+00:00"}