{"created":"2023-06-20T15:15:03.588649+00:00","id":45106,"links":{},"metadata":{"_buckets":{"deposit":"eb322bf5-c961-4fca-8939-1e4bbbb7cf48"},"_deposit":{"created_by":1,"id":"45106","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"45106"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00045106","sets":["1887:1893","1896:1898:1913:1917"]},"author_link":["472961","472960","472957","472959","472956","472958"],"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1984-12","bibliographicIssueDateType":"Issued"},"bibliographicPageStart":"10","bibliographicVolumeNumber":"848T","bibliographic_titles":[{},{"bibliographic_title":"Technical Report of National Aerospace Laboratory TR-848T","bibliographic_titleLang":"en"}]}]},"item_3_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"大きな開口面積比のロケットノズル内へ送入した二次流の有効比推力を実験的に求めた。推力4KN,燃焼室圧力3.5MPaの水素/酸素ロケット推力室を用い,出口開口面積比140:1のノズルにおいて,開口比13:1の位置で,30個の横長の噴出口から常温の水素ガスを送入した。二次流の主流に対する質量流量比1～5％の範囲で実験をおこなった。推力測定による二次流の有効比推力の測定の他に,ノズル静圧,ならびに壁面への熱流束の分布におよぼす二次流の効果も実験した。簡単な理論による二次流の有効比推力の計算値と実験値の比較をおこなった。二次流量が主流の2％以上では実験値は計算値よりも約20％高かった。二次流によるフィルム冷却の効果は大きく,ノズル出口にまでおよんだ。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"The effective specific impulse of secondary flow injected into a supersonic portion of a large-area ratio nozzle was evaluated experimentally. An oxygen/hydrogen thrust chamber with a 4000N thrust level and a chamber pressure of 3.5MPa was used. The secondary flow (ambient temperature hydrogen as a simulant of the oxygen/hydrogen turbine exhaust gas mixture) was injected through 30 discrete holes at a 13:1 local area ratio into a nozzle with a 140:1 overall area ratio. The mass flow ratio of secondary flow to primary flow was varied from 1 to 5％. Using a simple theory, experimentally obtained effective secondary flow specific impulse Is was compared with calculated results. The experimental Is value was consistently higher than the calculated value by about 20％, presumably because of mixing and heat transfer effects which were not taken into account in the theoretical calculation. The secondary flow film cooling effect was substantial and persisted up to the nozzle exit.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: NALTR0848000","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-848T","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":"0389-4010","subitem_source_identifier_type":"ISSN"}]},"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角田支所"},{"subitem_text_value":"航空宇宙技術研究所角田支所"},{"subitem_text_value":"宇宙開発事業団"}]},"item_3_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"Kakuda Branch Office, National Aerospace Laboratory(NAL)"},{"subitem_text_language":"en","subitem_text_value":"Kakuda Branch Office, National Aerospace Laboratory(NAL)"},{"subitem_text_language":"en","subitem_text_value":"National Space Development Agency of Japan(NASDA)"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"宮島, 博"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"日下, 和夫"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"十亀, 英司"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"MIYAJIMA, Hiroshi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"KUSAKA, Kazuo","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"SOGAME, Eiji","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":"naltr0848t.pdf","filesize":[{"value":"973.6 kB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"naltr0848t.pdf","url":"https://jaxa.repo.nii.ac.jp/record/45106/files/naltr0848t.pdf"},"version_id":"c03dfc2a-98d3-43fa-908e-6675d2f0fe76"}]},"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":"Effective Specific Impulse of Secondary Flow Injected into a Rocket Nozzle","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"Effective Specific Impulse of Secondary Flow Injected into a Rocket Nozzle","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":"45106","relation_version_is_last":true,"title":["Effective Specific Impulse of Secondary Flow Injected into a Rocket Nozzle"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T21:45:11.776686+00:00"}