{"created":"2023-06-20T15:07:58.506543+00:00","id":37354,"links":{},"metadata":{"_buckets":{"deposit":"1b328ab4-bb7f-4c98-b14e-e80e32052b46"},"_deposit":{"created_by":1,"id":"37354","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"37354"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00037354","sets":["1887:1891","1896:1898:1913:1915"]},"author_link":["480318","480312","480314","480315","480320","480313","480321","480316","480317","480319"],"item_5_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Study on supersonic laminar flow control on a warped delta wing"}]},"item_5_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1999-02","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"264","bibliographicPageStart":"259","bibliographicVolumeNumber":"41","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 24-26 Jun. 1998 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 24-26 Jun. 1998 Tokyo Japan","subitem_description_type":"Other"}]},"item_5_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"超音速輸送機(SST)の揚抗比改善のためには摩擦抗力を低減する必要があるので、実際の空気動力学的設計への応用の観点から、Warp形状翼に関する超音速層流制御効果について検討してきた。今回、実験によりマッハ数M=1.4における吸い込みに起因する大幅な低減を実験的に確認し、また層流境界層の安定性を数値計算的に解析した。","subitem_description_type":"Abstract"}]},"item_5_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"Since the friction drag of an SST (Supersonic Transport) must be reduced to improve the lift-to-drag ratio, supersonic laminar flow control on a warped wing has been investigated from a viewpoint of applying it to real aerodynamic design. Then large reduction due to suction at M = 1.4 was experimentally confirmed and the stability of laminar boundary layer was numerically analyzed.","subitem_description_type":"Other"}]},"item_5_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0001958040","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-41","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 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