{"created":"2023-06-20T15:15:21.099870+00:00","id":45426,"links":{},"metadata":{"_buckets":{"deposit":"dd66b1a2-b8df-4f7b-b05d-0c566ae240d4"},"_deposit":{"created_by":1,"id":"45426","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"45426"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00045426","sets":["1887:1893","1896:1898:1913:1917"]},"author_link":["474735","474733","474737","474731","474739","474736","474732","474741","474742","474734","474740","474738"],"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"2002-01","bibliographicIssueDateType":"Issued"},"bibliographicPageStart":"15","bibliographicVolumeNumber":"1442T","bibliographic_titles":[{"bibliographic_title":"独立行政法人航空宇宙技術研究所報告"},{"bibliographic_title":"Technical Report of National Aerospace Laboratory TR-1442T","bibliographic_titleLang":"en"}]}]},"item_3_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"ラムジェットエンジン試験設備（RJTF）におけるマッハ８条件でのスクラムジェットエンジン模型の燃焼性能を改善するために、幅46mmのストラットを新規に取り付け収縮比を8.3に上げて試験を行った。エンジン出口でのガス採取結果によると、当量比0.8条件で燃焼効率は約90%であった。回復温度の高い天板上の低速域への燃料垂直噴射が、着火に対して有効であり、ストラットによる昇圧が燃焼に対して有効であることがわかった。気流状態からの推力増分は当量比1.2条件で420Nであった。低推力レベルであった原因は、高マッハ数の拡大部での燃焼による高いRayleigh 総圧損失と、ストラットでの大きなベース抗力である。ステップ上流からの少量の燃料噴射により燃焼状態は大きく変化した。燃料を平行噴射した場合の燃焼による推力増分は僅かであった。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"In order to improve combustion performance in a hydrogen-fueled scramjet research engine model for the Mach 8 flight condition, a thick strut was attached and the contraction ratio was increased to 8.3. According to the result of the gas-sampling at the exit of the model, a combustion efficiency of 90% was attained for the fuel flow rate φ=0.8. Normal fuel injection into the low-velocity region on the top wall, in which the recovery temperature was high, was found to be effective for ignition. The high pressure in the combustor caused by the thick strut was also found to be effective for combustion. The thrust increase from the no-fueled condition was 420 N for φ=1.2. The relatively low thrust level was caused by the Rayleigh heating loss and the base drag of the strut.  Small amounts of fuel injection upstream of the step changed the combustion condition significantly, however controlled engine operation was difficult to achieve. Parallel fuel injection resulted in very poor combustion for this engine model.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: NALTR1442000","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-1442T","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":"1347-4588","subitem_source_identifier_type":"ISSN"}]},"item_3_source_id_24":{"attribute_name":"書誌レコードID","attribute_value_mlt":[{"subitem_source_identifier":"AN00311347","subitem_source_identifier_type":"NCID"}]},"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ラムジェット推進研究センター"},{"subitem_text_value":"航空宇宙技術研究所ラムジェット推進研究センター"},{"subitem_text_value":"航空宇宙技術研究所ラムジェット推進研究センター"},{"subitem_text_value":"宇宙開発事業団"},{"subitem_text_value":"航空宇宙技術研究所ラムジェット推進研究センター"},{"subitem_text_value":"航空宇宙技術研究所ラムジェット推進研究センター"}]},"item_3_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"Ramjet Propulsion Research Center, National Aerospace Laboratory(NAL)"},{"subitem_text_language":"en","subitem_text_value":"Ramjet Propulsion Research Center, National Aerospace Laboratory(NAL)"},{"subitem_text_language":"en","subitem_text_value":"Ramjet Propulsion Research Center, National Aerospace Laboratory(NAL)"},{"subitem_text_language":"en","subitem_text_value":"National Space Development Agency of Japan(NASDA)"},{"subitem_text_language":"en","subitem_text_value":"Ramjet Propulsion Research Center, National Aerospace Laboratory(NAL)"},{"subitem_text_language":"en","subitem_text_value":"Ramjet Propulsion Research Center, National Aerospace Laboratory(NAL)"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"苅田, 丈士"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"工藤, 賢司"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"泉川, 宗男"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"桜中, 登"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"小野, 文衛"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"佐藤, 茂"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"KANDA, Takeshi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"KUDO, Kenji","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"IZUMIKAWA, Muneo","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"SAKURANAKA, Noboru","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"ONO, Fumiei","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"SATOH, Shigeru","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":"naltr0001442t.pdf","filesize":[{"value":"752.8 kB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"naltr0001442t.pdf","url":"https://jaxa.repo.nii.ac.jp/record/45426/files/naltr0001442t.pdf"},"version_id":"bbc1ff8b-c398-4828-b8a3-980b33808fa3"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"scramjet, strut","subitem_subject_language":"en","subitem_subject_scheme":"Other"}]},"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":"RJTF Mach 8 Testing of a Scramjet Engine Model of a Contraction Ratio of 8.3 with a Strut","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"RJTF Mach 8 Testing of a Scramjet Engine Model of a Contraction Ratio of 8.3 with a Strut","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":"45426","relation_version_is_last":true,"title":["RJTF Mach 8 Testing of a Scramjet Engine Model of a Contraction Ratio of 8.3 with a Strut"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T21:39:41.886032+00:00"}