{"created":"2023-06-20T15:16:14.618898+00:00","id":46354,"links":{},"metadata":{"_buckets":{"deposit":"e4ce1be2-9822-49c8-9ccf-35394d11dc21"},"_deposit":{"created_by":1,"id":"46354","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"46354"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00046354","sets":["1398:1530:2040","1543:1874:2045","1887:1891","9:789:790:2039"]},"author_link":["514097","514094","514095","514096"],"item_5_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Flow-path Design of a Combustor Model for a Supersonic-combustion Flight Experiment"}]},"item_5_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"2020-02-04","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"164","bibliographicPageStart":"157","bibliographicVolumeNumber":"JAXA-SP-19-007","bibliographic_titles":[{"bibliographic_title":"宇宙航空研究開発機構特別資料: 第51回流体力学講演会/第37回航空宇宙数値シミュレーション技術シンポジウム論文集"},{"bibliographic_title":"JAXA Special Publication: Proceedings of the 51st Fluid Dynamics Conference / the 37th Aerospace Numerical Simulation Symposium","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":"第51回流体力学講演会/第37回航空宇宙数値シミュレーション技術シンポジウム (2019年7月1日-3日. 早稲田大学早稲田キャンパス国際会議場), 新宿区, 東京","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":"51st Fluid Dynamics Conference / the 37th Aerospace Numerical Simulation Symposium (July 1-3, 2019. International Conference Center, Waseda University), Shinjuku-ku, Tokyo, Japan","subitem_description_type":"Other"}]},"item_5_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"A flight-ground test comparison program is undergoing at JAXA to reveal so-called facility effects on hypersonic aerodynamics and combustion phenomena. The flight test vehicle will mount a combustor duct along its centerline, with so-called alligator type inlet with side-spillage to attain good starting characteristics. In the present paper, parametric study on flow-path design of the combustor model was conducted by CFD to examine influences of the geometry parameters, such as configurations of fuel injector holes and geometry of a flame-holding cavity, on combustion characteristics and to settle the design guideline which could enhance so-called vitiation effects on combustion. A two-staged fuel injection scheme was adopted for the combustor model and the first-stage and second-stage injection holes were installed at upstream and downstream of the flame-holding cavity, respectively. The results showed that a distance between the first-stage injection hole and the flame-holding cavity as well as the number of the injector holes at each stage would have strong influence on the combustor flow-field and its characteristics while the depth of the flame-holding cavity would have little influence.","subitem_description_type":"Other"}]},"item_5_description_18":{"attribute_name":"内容記述","attribute_value_mlt":[{"subitem_description":"形態: カラー図版あり","subitem_description_type":"Other"}]},"item_5_description_19":{"attribute_name":"内容記述（英）","attribute_value_mlt":[{"subitem_description":"Physical characteristics: Original contains color illustrations","subitem_description_type":"Other"}]},"item_5_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA1930011013","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: JAXA-SP-19-007","subitem_description_type":"Other"}]},"item_5_publisher_8":{"attribute_name":"出版者","attribute_value_mlt":[{"subitem_publisher":"宇宙航空研究開発機構(JAXA)"}]},"item_5_publisher_9":{"attribute_name":"出版者（英）","attribute_value_mlt":[{"subitem_publisher":"Japan Aerospace Exploration Agency (JAXA)"}]},"item_5_source_id_22":{"attribute_name":"ISSNONLINE","attribute_value_mlt":[{"subitem_source_identifier":"2433-2232","subitem_source_identifier_type":"ISSN"}]},"item_5_text_6":{"attribute_name":"著者所属","attribute_value_mlt":[{"subitem_text_value":"宇宙航空研究開発機構(JAXA)"},{"subitem_text_value":"宇宙航空研究開発機構(JAXA)"}]},"item_5_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"Japan Aerospace Exploration Agency (JAXA)"},{"subitem_text_language":"en","subitem_text_value":"Japan Aerospace Exploration Agency (JAXA)"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"髙橋, 政浩"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"富岡, 定毅"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Takahashi, Masahiro","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Tomioka, Sadatake","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":"2020-03-27"}],"displaytype":"detail","filename":"AA1930011013.pdf","filesize":[{"value":"2.3 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"AA1930011013.pdf","url":"https://jaxa.repo.nii.ac.jp/record/46354/files/AA1930011013.pdf"},"version_id":"baa02fb2-f851-4b51-b6b6-f4060f87c3a6"}]},"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":"超音速燃焼飛行試験に用いる燃焼器流路形状の検討","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"超音速燃焼飛行試験に用いる燃焼器流路形状の検討"}]},"item_type_id":"5","owner":"1","path":["1891","2039","2040","2045"],"pubdate":{"attribute_name":"公開日","attribute_value":"2020-02-04"},"publish_date":"2020-02-04","publish_status":"0","recid":"46354","relation_version_is_last":true,"title":["超音速燃焼飛行試験に用いる燃焼器流路形状の検討"],"weko_creator_id":"1","weko_shared_id":1},"updated":"2023-06-20T20:13:29.882286+00:00"}