{"created":"2023-06-20T15:13:55.575941+00:00","id":43896,"links":{},"metadata":{"_buckets":{"deposit":"a8f6f40f-7977-4ed0-8ffb-461bfdf6915c"},"_deposit":{"created_by":1,"id":"43896","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"43896"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00043896","sets":["1887:1893","1896:1898:1913:1916"]},"author_link":["466205","466206","466204","466202","466201","466203"],"item_3_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Design Calculation of Diffusers for Rocket Engine Altitude Simulation"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1976-09","bibliographicIssueDateType":"Issued"},"bibliographicPageStart":"36","bibliographicVolumeNumber":"313","bibliographic_titles":[{"bibliographic_title":"航空宇宙技術研究所資料"},{"bibliographic_title":"Technical Memorandum of National Aerospace Laboratory","bibliographic_titleLang":"en"}]}]},"item_3_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"筆者らが,ロケットエンジン高空性能試験用エゼクタの実験的研究をおこなった過程で使用した計算法のうち,簡単で設計に直接使用できるものについて述べた。スタート圧力比についてはGermanらの方法をプログラム化し,各種パラメタの効果を計算するとともに,いくつかの問題点を示した。低圧室圧力比に関しては,ONERAのグループによって提案された再付着角度の考えをもとにして新しい再付着角度相関式を求めた。この相関式を用いる低圧式圧力の計算法について述べ,この方法の採用によって低圧室圧力の予測の改良がなされることを示した。プログラムリストを付録に示す。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"This paper describes two methods directly applicable to zero-secondary-flow ejector design from the calculation methods employed by the authors during the experimental studies on ejectors for rocket engine altitude simulation. One method is that of predicting the starting pressure ratio of a second throat diffuser, de- veloped by German et al. This method is computerized and a parametric study was conducted. The other concerns a better method of predicting the capsule pressure ratio based on the angular reattachment criteria of ONERA group. New angular reattachment criteria for large area ratio nozzles are correlated using available experimental data. Calculated results are shown to be in satisfactory agreement with the NAL data. Program lists are given in the appendix.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: NALTM0313000","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 TM-313","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":"0452-2982","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":"AN00314334","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角田支所"},{"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"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"宮島, 博"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"阿部, 登"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"木皿, 且人"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"MIYAJIMA, Hiroshi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"ABE, Noboru","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"KISARA, Katsuto","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":"2020-01-28"}],"displaytype":"detail","filename":"naltm00313.pdf","filesize":[{"value":"1.8 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"naltm00313.pdf","url":"https://jaxa.repo.nii.ac.jp/record/43896/files/naltm00313.pdf"},"version_id":"95969000-6a1a-4e1c-a66b-ce445db891c0"}]},"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":"technical report","resourceuri":"http://purl.org/coar/resource_type/c_18gh"}]},"item_title":"ロケット・エンジン高空性能試験用デュフィーザの設計計算","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"ロケット・エンジン高空性能試験用デュフィーザの設計計算"}]},"item_type_id":"3","owner":"1","path":["1893","1916"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"43896","relation_version_is_last":true,"title":["ロケット・エンジン高空性能試験用デュフィーザの設計計算"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T22:06:01.366436+00:00"}