{"created":"2023-06-20T14:36:26.689754+00:00","id":2755,"links":{},"metadata":{"_buckets":{"deposit":"6e8b56c8-b7dc-4825-af05-891bbd7e64b4"},"_deposit":{"created_by":1,"id":"2755","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"2755"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00002755","sets":["1887:1893","9:1090:1333:1338"]},"author_link":["8797","8802","8800","8798","8801","8799"],"item_3_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Wind tunnel test of the NEXST2 supersonic intake mounted underneath a wing"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"2004-03-25","bibliographicIssueDateType":"Issued"},"bibliographicVolumeNumber":"JAXA-RM-03-027","bibliographic_titles":[{"bibliographic_title":"宇宙航空研究開発機構研究開発資料"},{"bibliographic_title":"JAXA Research and Development Memorandum","bibliographic_titleLang":"en"}]}]},"item_3_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"航空宇宙技術研究所が開発を進めているジェットエンジンを搭載した小型超音速実験機(ジェット実験機)には、マッハ2までの飛行速度で作動する2次元外部圧縮型可変形状超音速インテークを搭載する予定としている。本試験は、そのジェット実験機用超音速インテーク設計の一環として行われたものである。インテークの空力性能取得には、インテークを、機体と統合した状態で、実際の飛行マッハ数や迎え角、横滑り角のもとで行う試験(以下「インテーク機体統合試験」)が必要である。ただし、このような機体と統合した状態の風洞試験に先立って、インテークのみを風洞に設置して一様流を流入させて性能を取得する試験(以下「単体試験」)が行われる。ジェット実験機用インテークの設計においても、単体試験を実施した。本研究では、インテーク機体統合試験の予備段階として、インテークを「模擬翼」の下に取り付けて試験を行い、「模擬翼」によるインテーク入口流れの変化が空力性能に与える影響を風洞試験で調べた。その結果、主流マッハ数0.6≦M(sub ∞)≦1.05では、迎角の上昇と共に、カウルリップ剥離の影響によって、臨界点付近で総圧損失とディストーションが増大することがわかった。主流マッハ数1.2≦M(sub ∞)≦1.4では、迎角の上昇とともにインテーク入口マッハ数が減少することによる、亜臨界作動状態での総圧回復率の向上と、亜臨界側安定作動マージンの増大が見られた。主流マッハ数M(sub ∞)≧1.7でも、迎角の上昇とともに臨界点から亜臨界作動状態での総圧回復率の上昇が確認されたが、衝撃波3重点から発生するせん断層が流入する流量比が、臨界点の流量比より速いペースで上昇することがわかった。この影響で、主流マッハ数M(sub ∞)=2.0では、迎角の上昇とともに、Ferri型のバズが発生する流量比、および、亜臨界側作動マージンが減少する傾向が見られた。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"The Jet-Powered Supersonic Experimental Airplane (NEXST-2), being developed by National Aerospace Laboratory (NAL), will have a high-speed propulsion system featuring a two-dimensional external compression air-intake with variable ramps. The aerodynamic performance of the air-intake mounted underneath a wing at transonic and supersonic flight conditions was obtained by wind tunnel tests. Wind tunnel test were performed in a Mach number range of 0.6 to 2.1 at the 2 m x 2 m Transonic Wind Tunnel and the 1 m x 1 m Supersonic Wind Tunnel at NAL. The wind tunnel model was a 19.2 percent scale C313 air-intake model mounted underneath a wing. At the upstream Mach numbers ranging from 0.6 to 1.05, the pressure recovery at critical operation decreased with the increasing angle of attack, due to the separation around the lip of the cowl. At moderate Mach numbers 1.2 less than or equal to M(sub infinity) less than or equal to 1.4, both of an increase in the pressure recovery and resistance to the occurrence of the flow instability, buzz, were observed as the angle of attack increased. These phenomena were mainly due to the reduced inlet Mach number which weakened the shock-boundary layer interaction on the ramp for supersonic compression. At upstream Mach numbers of 1.7 or more, the shear layer originating from the shock intersection point was ingested at a higher mass flow rate at a higher angle of attack, causing a reduced stable mass flow range at higher angle of attack at M(sub infinity) = 2.0.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0047422000","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: JAXA-RM-03-027","subitem_description_type":"Other"}]},"item_3_publisher_8":{"attribute_name":"出版者","attribute_value_mlt":[{"subitem_publisher":"宇宙航空研究開発機構"}]},"item_3_publisher_9":{"attribute_name":"出版者（英）","attribute_value_mlt":[{"subitem_publisher":"Japan Aerospace Exploration Agency (JAXA)"}]},"item_3_source_id_21":{"attribute_name":"ISSN","attribute_value_mlt":[{"subitem_source_identifier":"1349-1121","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":"AA11983593","subitem_source_identifier_type":"NCID"}]},"item_3_text_6":{"attribute_name":"著者所属","attribute_value_mlt":[{"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"},{"subitem_text_value":"宇宙航空研究開発機構 総合技術研究本部"}]},"item_3_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 Technology and Aeronautics"},{"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":"藤原, 仁志"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"村上, 哲"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"渡辺, 安"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Fujiwara, Hitoshi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Murakami, Akira","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Watanabe, Yasushi","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":"2020-01-15"}],"displaytype":"detail","filename":"47422000.pdf","filesize":[{"value":"7.0 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"47422000.pdf","url":"https://jaxa.repo.nii.ac.jp/record/2755/files/47422000.pdf"},"version_id":"772657d0-d4d8-478f-987e-bcd2f92eaf95"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"風洞試験","subitem_subject_scheme":"Other"},{"subitem_subject":"空力特性","subitem_subject_scheme":"Other"},{"subitem_subject":"可変ランプ","subitem_subject_scheme":"Other"},{"subitem_subject":"エアインテーク","subitem_subject_scheme":"Other"},{"subitem_subject":"外部圧縮","subitem_subject_scheme":"Other"},{"subitem_subject":"超音速風洞","subitem_subject_scheme":"Other"},{"subitem_subject":"衝撃波・境界層相互作用","subitem_subject_scheme":"Other"},{"subitem_subject":"流れの可視化","subitem_subject_scheme":"Other"},{"subitem_subject":"wind tunnel test","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"aerodynamic characteristic","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"variable ramp","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"air intake","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"external compression","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"supersonic wind tunnel","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"shock-boundary layer interaction","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"flow visualization","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":"technical report","resourceuri":"http://purl.org/coar/resource_type/c_18gh"}]},"item_title":"模擬翼の下に取り付けたジェット実験機超音速インテークの空力特性取得風洞試験","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"模擬翼の下に取り付けたジェット実験機超音速インテークの空力特性取得風洞試験"}]},"item_type_id":"3","owner":"1","path":["1338","1893"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"2755","relation_version_is_last":true,"title":["模擬翼の下に取り付けたジェット実験機超音速インテークの空力特性取得風洞試験"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-21T09:16:36.191118+00:00"}