{"created":"2023-06-20T15:16:14.827086+00:00","id":46357,"links":{},"metadata":{"_buckets":{"deposit":"88989acc-8a59-4153-badf-c834f56ddd72"},"_deposit":{"created_by":1,"id":"46357","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"46357"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00046357","sets":["1398:1530:2040","1543:1874:2045","1887:1891","9:789:790:2039"]},"author_link":["514122","514118","514119","514123","514121","514120"],"item_5_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Effects of Flight Conditions and Attitudes on Thrust Performance of Hypersonic Aircraft Equipped with Airframe-Integrated Linear-Spike Nozzles"}]},"item_5_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"2020-02-04","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"191","bibliographicPageStart":"183","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":"The airframe-integrated linear-spike nozzle concept applied to an external nozzle for high-speed aircraft was evaluated with regard to the thrust augmentation capability in the various angles and ambient air conditions. The baseline airframe geometry was first premised to be a hypersonic waverider design. The main focus was on the vehicle aftbody. The baseline aftbody case had an external nozzle comprised of a simple divergent nozzle. The external nozzle section was hypothetically replaced with linear-spike external nozzle configurations. Performance evaluation was mainly conducted by considering the nozzle thrust generated by the pressure distribution on the external nozzle surface at the aftbody portion calculated by computer simulation at various flight conditions under angles of attack and ambient pressures. The thrust performance of the proposed linear-spike external nozzle concept was nearly equivalent to that of the baseline geometry at cruise conditions though the wall surface area can be significantly reduced. This is because the design of the proposed concept had a compression wall for the exhaust flow, which resulted in increasing the wall pressure. With this insight, the configuration with the double-ramp exhibited a potential for further improvement in thrust performance. Further potential was shown with the proposed linear-spike configuration in thrust performance under angled flight conditions as well as off-design flight conditions. Thus, benefits were obtained by employing the airframe-integrated linear-spike external nozzle concept.","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: AA1930011016","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":"株式会社日立ソリューションズ東日本"},{"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":"Hitachi Solutions East Japan, Ltd."},{"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, 英美"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"宗像, 利彦"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"佐藤, 茂"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Takahashi, Hidemi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Munakata, Toshihiko","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Sato, 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":"2020-03-27"}],"displaytype":"detail","filename":"AA1930011016.pdf","filesize":[{"value":"2.2 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"AA1930011016.pdf","url":"https://jaxa.repo.nii.ac.jp/record/46357/files/AA1930011016.pdf"},"version_id":"3e00c96a-db60-4584-93e2-f6360591ee69"}]},"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":"極超音速機外部ノズルの性能に対する飛行条件の影響評価","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"極超音速機外部ノズルの性能に対する飛行条件の影響評価"}]},"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":"46357","relation_version_is_last":true,"title":["極超音速機外部ノズルの性能に対する飛行条件の影響評価"],"weko_creator_id":"1","weko_shared_id":1},"updated":"2023-06-20T20:13:27.022044+00:00"}