{"created":"2022-10-13T06:15:34.492600+00:00","id":2003924,"links":{},"metadata":{"_buckets":{"deposit":"f8ae688d-6e58-468c-8f6e-04b0d36f09a9"},"_deposit":{"created_by":17,"id":"2003924","owner":"17","owners":[17],"owners_ext":{"displayname":"repository","username":"repository"},"pid":{"revision_id":0,"type":"depid","value":"2003924"},"status":"published"},"_oai":{"id":"oai:nagoya.repo.nii.ac.jp:02003924","sets":["673:674:675"]},"author_link":[],"control_number":"2003924","item_1615768549627":{"attribute_name":"出版タイプ","attribute_value_mlt":[{"subitem_version_resource":"http://purl.org/coar/version/c_ab4af688f83e57aa","subitem_version_type":"AM"}]},"item_1629683748249":{"attribute_name":"日付","attribute_value_mlt":[{"subitem_date_issued_datetime":"2022-10-13","subitem_date_issued_type":"Available"}]},"item_9_biblio_info_6":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"2022-07","bibliographicIssueDateType":"Issued"},"bibliographicIssueNumber":"7","bibliographicPageEnd":"4023","bibliographicPageStart":"4015","bibliographicVolumeNumber":"60","bibliographic_titles":[{"bibliographic_title":"AIAA Journal","bibliographic_titleLang":"en"}]}]},"item_9_description_4":{"attribute_name":"内容記述","attribute_value_mlt":[{"subitem_description":"Converging–diverging nozzles are common in rocket engine systems to increase the exhaust velocity and improve thrust performance. In this study, we focused on the acceleration of subsonic burned gas without a structural throat via detonation to realize a simple and compact engine. We developed and tested a rotating detonation engine (RDE) without a throat and with a diverging channel (constant diverging angle α=5  deg). Gaseous C2H4 and O2 were used as the propellants, and the mass flow rate ranged from 62 to 134  g/s in the combustion tests under low back-pressure conditions. We measured pressure and thrust, as well as high-speed imaging of self-luminescence of the combustion and imaging of the exhaust plume. The pressure at the exit was less than one-fifth of the maximum pressure in the RDE, significantly below the value for a sonic flow. The results suggested that the exhaust flow was supersonic, with values up to Mach 1.7, without the need of a converging section within the engine. In addition to the estimated Mach number from the measured pressure, the exhaust plume images coherently indicated the existence of supersonic exhaust.","subitem_description_language":"en","subitem_description_type":"Abstract"}]},"item_9_publisher_32":{"attribute_name":"出版者","attribute_value_mlt":[{"subitem_publisher":"American Institute of Aeronautics and Astronautics","subitem_publisher_language":"en"}]},"item_9_relation_43":{"attribute_name":"関連情報","attribute_value_mlt":[{"subitem_relation_type":"isVersionOf","subitem_relation_type_id":{"subitem_relation_type_id_text":"https://doi.org/10.2514/1.J061300","subitem_relation_type_select":"DOI"}}]},"item_9_source_id_7":{"attribute_name":"収録物識別子","attribute_value_mlt":[{"subitem_source_identifier":"0001-1452","subitem_source_identifier_type":"PISSN"}]},"item_access_right":{"attribute_name":"アクセス権","attribute_value_mlt":[{"subitem_access_right":"open access","subitem_access_right_uri":"http://purl.org/coar/access_right/c_abf2"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"Nakata, Kotaro","creatorNameLang":"en"}]},{"creatorNames":[{"creatorName":"Ota, Kosei","creatorNameLang":"en"}]},{"creatorNames":[{"creatorName":"Ito, Shiro","creatorNameLang":"en"}]},{"creatorNames":[{"creatorName":"Ishihara, Kazuki","creatorNameLang":"en"}]},{"creatorNames":[{"creatorName":"Goto, Keisuke","creatorNameLang":"en"}]},{"creatorNames":[{"creatorName":"Itouyama, Noboru","creatorNameLang":"en"}]},{"creatorNames":[{"creatorName":"Watanabe, Hiroaki","creatorNameLang":"en"}]},{"creatorNames":[{"creatorName":"Kawasaki, Akira","creatorNameLang":"en"}]},{"creatorNames":[{"creatorName":"Matsuoka, Ken","creatorNameLang":"en"}]},{"creatorNames":[{"creatorName":"Kasahara, Jiro","creatorNameLang":"en"}]},{"creatorNames":[{"creatorName":"Matsuo, Akiko","creatorNameLang":"en"}]},{"creatorNames":[{"creatorName":"Funaki, Ikkoh","creatorNameLang":"en"}]},{"creatorNames":[{"creatorName":"Higashino, Kazuyuki","creatorNameLang":"en"}]},{"creatorNames":[{"creatorName":"Braun, James","creatorNameLang":"en"}]},{"creatorNames":[{"creatorName":"Meyer, Terrence","creatorNameLang":"en"}]},{"creatorNames":[{"creatorName":"Paniagua, Guillermo","creatorNameLang":"en"}]}]},"item_files":{"attribute_name":"ファイル情報","attribute_type":"file","attribute_value_mlt":[{"accessrole":"open_access","date":[{"dateType":"Available","dateValue":"2022-10-13"}],"displaytype":"detail","filename":"AIAAJournal_revision_without_correction_footnote_forRepository.pdf","filesize":[{"value":"3.8 MB"}],"format":"application/pdf","mimetype":"application/pdf","url":{"objectType":"fulltext","url":"https://nagoya.repo.nii.ac.jp/record/2003924/files/AIAAJournal_revision_without_correction_footnote_forRepository.pdf"},"version_id":"46190099-3172-40c5-a360-82d8e547146c"}]},"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":"journal article","resourceuri":"http://purl.org/coar/resource_type/c_6501"}]},"item_title":"Supersonic Exhaust from a Rotating Detonation Engine with Throatless Diverging Channel","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"Supersonic Exhaust from a Rotating Detonation Engine with Throatless Diverging Channel","subitem_title_language":"en"}]},"item_type_id":"40001","owner":"17","path":["675"],"pubdate":{"attribute_name":"PubDate","attribute_value":"2022-10-13"},"publish_date":"2022-10-13","publish_status":"0","recid":"2003924","relation_version_is_last":true,"title":["Supersonic Exhaust from a Rotating Detonation Engine with Throatless Diverging Channel"],"weko_creator_id":"17","weko_shared_id":-1},"updated":"2023-01-16T04:59:15.475272+00:00"}