{"created":"2023-06-20T14:36:06.698243+00:00","id":2411,"links":{},"metadata":{"_buckets":{"deposit":"bb3df04c-d112-4c68-b3cc-810a963143a2"},"_deposit":{"created_by":1,"id":"2411","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"2411"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00002411","sets":["1887:1893","9:10:368:387"]},"author_link":["6152","6151","6150","6149","6148","6153"],"item_3_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Effect of sidewall configurations on aerodynamic performance of supersonic air-intake"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"2004-03-25","bibliographicIssueDateType":"Issued"},"bibliographicVolumeNumber":"JAXA-RR-03-009","bibliographic_titles":[{"bibliographic_title":"宇宙航空研究開発機構研究開発報告"},{"bibliographic_title":"JAXA Research and Development Report","bibliographic_titleLang":"en"}]}]},"item_3_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"2次元超音速インテークでは、超音速ディフューザ部の側壁形状はインテークの空力性能に大きく影響をおよぼす部分であり、側壁形状が空力性能に及ぼす影響を明らかにすることを目的として、風洞試験およびCFD解析を実施した。側壁形状の影響が顕著に現れるマッハ1.5以上の条件に対して風洞試験を行ない、横流れ偏角やランプ可変形状が異なる条件における空力特性を取得し、側壁形状の影響を詳細に調べた。その結果、バズが発生するまでの亜臨界作動域における安定な作動域は側壁が大きいほど広く、性能が良いことが明らかとなった。一方、超臨界作動域では、マッハ数が高く側壁が大きいほど、また横流れ偏角が大きいほど亜音速ディフューザ内の流れは剥離しやすくなり、性能が低下することがわかった。さらにCFD解析により、インテークの流れ構造を詳細に調べた結果、側壁形状はサイドスピレージに影響を及ぼすため、インテークに流入する流管形状が変化し、その結果として、小さい側壁形状ではバズが発生しやすいことが明らかとなった。また、大きい側壁形状では衝撃波システムの逆圧力勾配の影響で、剥離しやすい境界層が亜音速ディフューザに流入することがわかった。そして、境界層の形状係数が有る程度以上になると、亜音速ディフューザ内で境界層剥離が生じ、空力性能が低下することが明らかとなった。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"The effects of sidewall configurations on the aerodynamic performance of two dimensional external compression supersonic air-intakes were investigated experimentally and numerically. The aerodynamic performance for various yaw angles and ramp angles was obtained by wind tunnel tests performed in the Mach number range of 1.5 to 2.0. It was found that the major advantage of an air-intake with a larger sidewall configuration is its wider stable range in subcritical operation. On the other hand, it also had the disadvantages of lower pressure recovery and larger spatial distortion, especially in supercritical operation, both of which were due to boundary layer separation in the subsonic diffuser. CFD results made it clear that the ingestion of the shear layer caused by shock-shock interaction occurred at a higher mass flow ratio in the smaller sidewall configuration, due to the change in the shape of the captured stream tube, which in turn is due to the increase in sideways spillage. It was also found that boundary layer separation in the subsonic diffuser depended on the shape factor of the boundary layer coming into the subsonic diffuser, which is affected by the interaction of the boundary layer on the sidewall surface with the shock system.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0047401000","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-RR-03-009","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":"1349-1113","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":"AA1192675X","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":"渡辺, 安"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"村上, 哲"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"藤原, 仁志"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Watanabe, Yasushi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Murakami, Akira","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Fujiwara, Hitoshi","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":"47401000.pdf","filesize":[{"value":"9.4 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"47401000.pdf","url":"https://jaxa.repo.nii.ac.jp/record/2411/files/47401000.pdf"},"version_id":"116cc9b8-a642-41ee-b16e-cf700cd735da"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"超音速流","subitem_subject_scheme":"Other"},{"subitem_subject":"超音速飛行","subitem_subject_scheme":"Other"},{"subitem_subject":"エアインテーク","subitem_subject_scheme":"Other"},{"subitem_subject":"空力特性","subitem_subject_scheme":"Other"},{"subitem_subject":"側壁形状","subitem_subject_scheme":"Other"},{"subitem_subject":"風洞試験","subitem_subject_scheme":"Other"},{"subitem_subject":"超音速風洞","subitem_subject_scheme":"Other"},{"subitem_subject":"CFD","subitem_subject_scheme":"Other"},{"subitem_subject":"supersonic flow","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"supersonic flight","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"air intake","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"aerodynamic characteristic","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"sidewall configuration","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"wind tunnel test","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"supersonic wind tunnel","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"CFD","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":"超音速インテークの空力性能に及ぼす側壁形状の影響","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"超音速インテークの空力性能に及ぼす側壁形状の影響"}]},"item_type_id":"3","owner":"1","path":["387","1893"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"2411","relation_version_is_last":true,"title":["超音速インテークの空力性能に及ぼす側壁形状の影響"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-21T09:23:03.439607+00:00"}