{"created":"2023-06-20T15:07:45.022624+00:00","id":37116,"links":{},"metadata":{"_buckets":{"deposit":"df692bb7-5474-4124-b9c1-7b40619362b3"},"_deposit":{"created_by":1,"id":"37116","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"37116"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00037116","sets":["1887:1891","1896:1898:1913:1915"]},"author_link":["478982","478984","478981","478983"],"item_5_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Boundary layer transition prediction problem in re-entry vehicle development"}]},"item_5_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1997-12","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"108","bibliographicPageStart":"105","bibliographicVolumeNumber":"36","bibliographic_titles":[{"bibliographic_title":"航空宇宙技術研究所特別資料"},{"bibliographic_title":"Special Publication of National Aerospace Laboratory","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":"航空宇宙技術研究所 26-28 Mar. 1997 東京 日本","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":"National Aerospace Laboratory 26-28 Mar. 1997 Tokyo Japan","subitem_description_type":"Other"}]},"item_5_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"境界層遷移予知に関連する問題を再突入機の熱空力設計について論じた。まず、風上境界層遷移特性を米国のシャトルとHYFLEX(極超音速飛行実験)飛行データに基づいて調査した。次いで、再突入機遷移の独特な特徴に関連した入手可能な風洞基礎実験の結果を概観した。頭部鈍頭度効果および迎角効果について主として論じた。これらの効果は頭部衝撃波の全圧力損失によるユニットレイノルズ数の減少、エントロピー層のswallowingによる境界層外縁流の条件変化、および飛行姿勢の変化に伴う衝撃波層の流れの形状変化に関連している。最後に、遷移メカニズムを明らかにするためには境界層不安定性に関する理論的・実験的研究における努力の重要性を強調した。","subitem_description_type":"Abstract"}]},"item_5_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"Problems associated with boundary layer transition prediction are discussed for aerothermal design of reentry vehicle. First, windward boundary layer transition characteristics are examined based on US shuttle and HYFLEX (Hypersonic Flight Experiment) flight data. Then, results of available basic wind tunnel experiments, which may be associated with distinctive feature of reentry vehicle transition, are reviewed. Nose bluntness and angle of attack effect are mainly discussed. These effects will related to unit Reynolds number reduction by nose shock total pressure loss, boundary layer edge flow condition change by entropy layer swallowing, and change of shock layer flow profile following change of flight attitude. Finally, importance of efforts in theoretical and experimental studies on boundary layer instability to clarify transition mechanism is emphasized.","subitem_description_type":"Other"}]},"item_5_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0001320026","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: NAL SP-36","subitem_description_type":"Other"}]},"item_5_publisher_8":{"attribute_name":"出版者","attribute_value_mlt":[{"subitem_publisher":"航空宇宙技術研究所"}]},"item_5_publisher_9":{"attribute_name":"出版者（英）","attribute_value_mlt":[{"subitem_publisher":"National Aerospace Laboratory (NAL)"}]},"item_5_source_id_21":{"attribute_name":"ISSN","attribute_value_mlt":[{"subitem_source_identifier":"0289-260X","subitem_source_identifier_type":"ISSN"}]},"item_5_source_id_24":{"attribute_name":"書誌レコードID","attribute_value_mlt":[{"subitem_source_identifier":"AN10097345","subitem_source_identifier_type":"NCID"}]},"item_5_text_6":{"attribute_name":"著者所属","attribute_value_mlt":[{"subitem_text_value":"航空宇宙技術研究所 空気力学部"},{"subitem_text_value":"航空宇宙技術研究所 空気力学部"}]},"item_5_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Aerodynamics Division"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Aerodynamics Division"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"穂積, 弘一"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"藤井, 啓介"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Hozumi, Koichi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Fujii, Keisuke","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":"2020-02-10"}],"displaytype":"detail","filename":"nalsp0036026.pdf","filesize":[{"value":"509.8 kB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"nalsp0036026.pdf","url":"https://jaxa.repo.nii.ac.jp/record/37116/files/nalsp0036026.pdf"},"version_id":"cbd29c08-4c81-4a06-9921-1823464543f4"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"再突入機","subitem_subject_scheme":"Other"},{"subitem_subject":"境界層遷移","subitem_subject_scheme":"Other"},{"subitem_subject":"熱空力設計","subitem_subject_scheme":"Other"},{"subitem_subject":"風洞試験","subitem_subject_scheme":"Other"},{"subitem_subject":"鈍頭度効果","subitem_subject_scheme":"Other"},{"subitem_subject":"迎角","subitem_subject_scheme":"Other"},{"subitem_subject":"ユニットレイノルズ数","subitem_subject_scheme":"Other"},{"subitem_subject":"全圧力損失","subitem_subject_scheme":"Other"},{"subitem_subject":"頭部衝撃波","subitem_subject_scheme":"Other"},{"subitem_subject":"境界層不安定性","subitem_subject_scheme":"Other"},{"subitem_subject":"reentry vehicle","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"boundary layer transition","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"aerothermal design","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"wind tunnel experiment","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"nose bluntness effect","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"angle of attack","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"unit Reynolds number","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"total pressure loss","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"nose shock","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"boundary layer instability","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":"conference paper","resourceuri":"http://purl.org/coar/resource_type/c_5794"}]},"item_title":"再突入機開発における境界層遷移予知の問題","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"再突入機開発における境界層遷移予知の問題"}]},"item_type_id":"5","owner":"1","path":["1891","1915"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"37116","relation_version_is_last":true,"title":["再突入機開発における境界層遷移予知の問題"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T21:25:36.209477+00:00"}