{"created":"2023-06-20T15:05:09.158347+00:00","id":34408,"links":{},"metadata":{"_buckets":{"deposit":"bbc48339-caf1-46e0-a8c8-194c30d4fddf"},"_deposit":{"created_by":1,"id":"34408","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"34408"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00034408","sets":["1887:1890","1896:1898:1899:1992"]},"author_link":["419552","419553"],"item_9_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1968-08","bibliographicIssueDateType":"Issued"},"bibliographicIssueNumber":"9","bibliographicPageEnd":"288-7","bibliographicPageStart":"209","bibliographicVolumeNumber":"33","bibliographic_titles":[{},{"bibliographic_title":"ISAS report/Institute of Space and Aeronautical Science,University of Tokyo","bibliographic_titleLang":"en"}]}]},"item_9_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"An investigation is made on the determination of shock wave drag of a body in a supersonic free stream of an ideal gas from the shape of the shock wave given either by theory or experiment. Assumption is made that the flow condition changes isentropically along each streamline behind the shock and the pressure regains the free stream value far behind the body. The total wave drag is obtained in a form of an integral of shock drag parameter, Φ which is a function of free stream Mach number and local shock angle, over entire shock surface. Numerical values of Φ are presented in tables and charts. Asymptotic solution of Φ in the far field is also given.","subitem_description_type":"Other"}]},"item_9_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: SA2400601000","subitem_description_type":"Other"}]},"item_9_publisher_8":{"attribute_name":"出版者","attribute_value_mlt":[{"subitem_publisher":"東京大学宇宙航空研究所"}]},"item_9_publisher_9":{"attribute_name":"出版者（英）","attribute_value_mlt":[{"subitem_publisher":"Institute of Space and Aeronautical Science,University of Tokyo"}]},"item_9_source_id_21":{"attribute_name":"ISSN","attribute_value_mlt":[{"subitem_source_identifier":"0372-1418","subitem_source_identifier_type":"ISSN"}]},"item_9_source_id_24":{"attribute_name":"書誌レコードID","attribute_value_mlt":[{"subitem_source_identifier":"AA00675986","subitem_source_identifier_type":"NCID"}]},"item_9_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"Hokkaido University of Education,Asahigawa Branch:Visiting Research Fellow at the Institute of Space and Aeronautical Science,University of Tokyo"},{"subitem_text_language":"en","subitem_text_value":"Hokkaido University of Education, Asahigawa Branch"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"SAWADA, Takashi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"YAMAGATA, Sekiji","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":"2020-01-24"}],"displaytype":"detail","filename":"SA2400601.pdf","filesize":[{"value":"9.2 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"SA2400601.pdf","url":"https://jaxa.repo.nii.ac.jp/record/34408/files/SA2400601.pdf"},"version_id":"27125651-2397-404a-977d-8855509972c6"}]},"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":"departmental bulletin paper","resourceuri":"http://purl.org/coar/resource_type/c_6501"}]},"item_title":"Equations, Tables and Charts for Shock Drag Parameter : Mach Number : 1.1∿15.0,Shock Angle : 90°∿Mach Angle","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"Equations, Tables and Charts for Shock Drag Parameter : Mach Number : 1.1∿15.0,Shock Angle : 90°∿Mach Angle","subitem_title_language":"en"}]},"item_type_id":"9","owner":"1","path":["1890","1992"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"34408","relation_version_is_last":true,"title":["Equations, Tables and Charts for Shock Drag Parameter : Mach Number : 1.1∿15.0,Shock Angle : 90°∿Mach Angle"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T23:42:39.854391+00:00"}