{"created":"2023-06-20T14:39:25.239969+00:00","id":6168,"links":{},"metadata":{"_buckets":{"deposit":"ee84073c-0e17-4caa-8477-b141cdb1077b"},"_deposit":{"created_by":1,"id":"6168","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"6168"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00006168","sets":["1887:1891","9:789:1031:1052"]},"author_link":["30896","30897","30899","30898","30895","30900"],"item_5_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Numerical investigations of the film cooling effect on rocket engine performance"}]},"item_5_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"2006-02-28","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"214","bibliographicPageStart":"209","bibliographicVolumeNumber":"JAXA-SP-05-017","bibliographic_titles":[{"bibliographic_title":"宇宙航空研究開発機構特別資料: 航空宇宙数値シミュレーション技術シンポジウム2005論文集"},{"bibliographic_title":"JAXA Special Publication: Proceedings of Aerospace Numerical Simulation Symposium 2005","bibliographic_titleLang":"en"}]}]},"item_5_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"LOX/LH2 subscale rocket nozzle flow fields are computationally simulated using three-dimensional compressible Navier-Stokes equations. The area ratio of the nozzle is 140 and film coolant hydrogen gases are injected from 30 film cooling holes which are distributed circumferentially at the area ratio of 13. The experimental nozzle throat Reynolds number indicates that the boundary layer of the nozzle is in its transition region as the size of the nozzle is small. Both the turbulent and laminar computations are carried out to investigate the effect of the boundary layer conditions to the nozzle performance. The computed results show that the structure of the separated flow down stream of the film cooling injection significantly changes between the turbulent and laminar conditions. Since clear difference in performance between the laminar and turbulent conditions are also shown, the computed result confirms that the experiment boundary layer condition is in its transition region. The nozzle wall temperature also influences the nozzle performance and the computed nozzle performance shows rather laminar flow performance when the film coolant temperature and the nozzle wall temperatures are set to be close.","subitem_description_type":"Other"}]},"item_5_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0049212035","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-05-017","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"}]},"item_5_publisher_9":{"attribute_name":"出版者（英）","attribute_value_mlt":[{"subitem_publisher":"Japan Aerospace Exploration Agency (JAXA)"}]},"item_5_source_id_21":{"attribute_name":"ISSN","attribute_value_mlt":[{"subitem_source_identifier":"1349-113X","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":"AA11984031","subitem_source_identifier_type":"NCID"}]},"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 宇宙科学研究本部"},{"subitem_text_value":"宇宙航空研究開発機構 総合技術研究本部"},{"subitem_text_value":"宇宙航空研究開発機構 総合技術研究本部"}]},"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 Institute of Space and Astronautical Science"},{"subitem_text_language":"en","subitem_text_value":"Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics"},{"subitem_text_language":"en","subitem_text_value":"Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"坪井, 伸幸"}],"nameIdentifiers":[{"nameIdentifier":"30895","nameIdentifierScheme":"WEKO"}]},{"creatorNames":[{"creatorName":"伊藤, 隆"}],"nameIdentifiers":[{"nameIdentifier":"30896","nameIdentifierScheme":"WEKO"}]},{"creatorNames":[{"creatorName":"宮島, 博"}],"nameIdentifiers":[{"nameIdentifier":"30897","nameIdentifierScheme":"WEKO"}]},{"creatorNames":[{"creatorName":"Tsuboi, Nobuyuki","creatorNameLang":"en"}],"nameIdentifiers":[{"nameIdentifier":"30898","nameIdentifierScheme":"WEKO"}]},{"creatorNames":[{"creatorName":"Ito, Takashi","creatorNameLang":"en"}],"nameIdentifiers":[{"nameIdentifier":"30899","nameIdentifierScheme":"WEKO"}]},{"creatorNames":[{"creatorName":"Miyajima, Hiroshi","creatorNameLang":"en"}],"nameIdentifiers":[{"nameIdentifier":"30900","nameIdentifierScheme":"WEKO"}]}]},"item_files":{"attribute_name":"ファイル情報","attribute_type":"file","attribute_value_mlt":[{"accessrole":"open_date","date":[{"dateType":"Available","dateValue":"2020-01-16"}],"displaytype":"detail","filename":"49212035.pdf","filesize":[{"value":"2.2 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"49212035.pdf","url":"https://jaxa.repo.nii.ac.jp/record/6168/files/49212035.pdf"},"version_id":"2d1b2f69-4692-4cd5-8c14-7381671f02e7"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"フィルム冷却","subitem_subject_scheme":"Other"},{"subitem_subject":"ロケットエンジン","subitem_subject_scheme":"Other"},{"subitem_subject":"数値解析","subitem_subject_scheme":"Other"},{"subitem_subject":"ナビエ-ストークス方程式","subitem_subject_scheme":"Other"},{"subitem_subject":"LE-5サブスケールエンジン","subitem_subject_scheme":"Other"},{"subitem_subject":"質量分率","subitem_subject_scheme":"Other"},{"subitem_subject":"速度ベクトル","subitem_subject_scheme":"Other"},{"subitem_subject":"マッハ数分布","subitem_subject_scheme":"Other"},{"subitem_subject":"層流","subitem_subject_scheme":"Other"},{"subitem_subject":"乱流","subitem_subject_scheme":"Other"},{"subitem_subject":"速度分布","subitem_subject_scheme":"Other"},{"subitem_subject":"film cooling","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"rocket engine","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"numerical analysis","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"Navier-Stokes equation","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"LE-5 subscale engine","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"mass fraction","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"velocity vector","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"Mach number distribution","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"laminar flow","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"turbulent flow","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"velocity distribution","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":"フィルム冷却を考慮した液酸・液水ロケットエンジン性能解析","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"フィルム冷却を考慮した液酸・液水ロケットエンジン性能解析"}]},"item_type_id":"5","owner":"1","path":["1052","1891"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"6168","relation_version_is_last":true,"title":["フィルム冷却を考慮した液酸・液水ロケットエンジン性能解析"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-21T08:00:53.388929+00:00"}