{"created":"2023-06-20T15:11:39.906595+00:00","id":41361,"links":{},"metadata":{"_buckets":{"deposit":"0b3e1c6f-76b4-4400-b8de-b53aeef6a176"},"_deposit":{"created_by":1,"id":"41361","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"41361"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00041361","sets":["1887:1893","1896:1898:1913:1915"]},"author_link":["489686","489687","489681","489680","489682","489683","489684","489685"],"item_3_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Boundary-layer transition measurements associated with NAL experimental SST project"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"2000-12","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"4","bibliographicPageStart":"1","bibliographicVolumeNumber":"47","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_3_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":"27-28 Sept. 1999 (25th). 27-28 Mar. 2000 (26th)","subitem_description_type":"Other"}]},"item_3_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":"27-28 Sept. 1999 (25th). 27-28 Mar. 2000 (26th)","subitem_description_type":"Other"}]},"item_3_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"CFD(数値流体力学)手法を用いて自然層流翼に適用することを意図したNALのSST(超音速輸送機)計画に関連して境界層遷移計測を実施した。実験の目的は最先端的な境界層遷移に関するデータベースを構築して翼上の遷移点予測の参考とし、また高度な計測技術を確立して航空機の飛行試験に適用することにある。本論文では、代表的な2つの予備実験の結果を報告した。ひとつはビーチクラフト機を使った飛行試験で、低乱流環境下における遷移過程を把握し、飛行試験の諸課題を明らかにするために実施した。Tollmien-Schlichting波が前縁近傍領域で検出され、スペクトルの振幅分布がSALLY(3次元層流境界層安定性解析)コードを使った数値予測値と非常によく一致したことから、風洞内で行う遷移計測が好結果を得ることが分かった。もうひとつは、超音速風洞内においてSST実験機の半裁模型に対して行った計測である。設計点、すなわち、迎角α=2.7度の時のマッハ数M=2では、層流状態は少なくともX/C=0.5に耐えることが分かった。自然層流翼はSST実験機の飛行試験で実現すると期待されている。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"Boundary-layer transition measurements have been conducted associated with the NAL SST (Supersonic Transport) project, which is designed to apply natural laminar flow wing using CFD (Computational Fluid Dynamics) technique. The purpose of experiments is to construct the database on boundary-layer transition most advanced which will be referred to predict the transition point on the wings, and to establish high quality measurement techniques, which will be applied to the flight test of the airplane. In this paper, the results of two typical preliminary experiments are introduced. One is flight tests using Beachcraft airplane, which are performed to grasp the transition process under low disturbance environment and to clarify the problems of flight test. Transition measurement as conducted in wind-tunnel was found to be successful, because Tollmien-Schlichting wave is detected at the region near the leading edge, and its amplitude distribution of the spectrum is in very good agreement with the numerical prediction by SALLY (3D laminar boundary layer stability analysis)-code. Another is the measurement on a half-model of SST experimental airplane in a supersonic wind tunnel. At the design point, i.e. Mach number M = 2 at an angle of attack alpha = 2.7 deg, it is found that the laminar state sustained at least to X/C = 0.5. Natural laminar flow wing is expected to realize on the flight test of SST experimental airplane.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0028636001","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: NAL SP-47","subitem_description_type":"Other"}]},"item_3_publisher_8":{"attribute_name":"出版者","attribute_value_mlt":[{"subitem_publisher":"航空宇宙技術研究所"}]},"item_3_publisher_9":{"attribute_name":"出版者（英）","attribute_value_mlt":[{"subitem_publisher":"National Aerospace Laboratory (NAL)"}]},"item_3_source_id_21":{"attribute_name":"ISSN","attribute_value_mlt":[{"subitem_source_identifier":"0289-260X","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":"AN10097345","subitem_source_identifier_type":"NCID"}]},"item_3_text_6":{"attribute_name":"著者所属","attribute_value_mlt":[{"subitem_text_value":"航空宇宙技術研究所"},{"subitem_text_value":"航空宇宙技術研究所"},{"subitem_text_value":"航空宇宙技術研究所"},{"subitem_text_value":"航空宇宙技術研究所"}]},"item_3_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"徳川, 直子"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"高木, 正平"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"西沢, 啓"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"杉浦, 裕樹"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Tokugawa, Naoko","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Takagi, Shohei","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Nishizawa, Akira","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Sugiura, Hiroki","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":"nalsp0047001.pdf","filesize":[{"value":"1.6 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"nalsp0047001.pdf","url":"https://jaxa.repo.nii.ac.jp/record/41361/files/nalsp0047001.pdf"},"version_id":"e1151e69-9ba1-41ce-be00-839ce06d50ef"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"SST実験機","subitem_subject_scheme":"Other"},{"subitem_subject":"超音速輸送機","subitem_subject_scheme":"Other"},{"subitem_subject":"境界層遷移","subitem_subject_scheme":"Other"},{"subitem_subject":"遷移計測","subitem_subject_scheme":"Other"},{"subitem_subject":"超音速流","subitem_subject_scheme":"Other"},{"subitem_subject":"飛行試験","subitem_subject_scheme":"Other"},{"subitem_subject":"自然層流翼","subitem_subject_scheme":"Other"},{"subitem_subject":"CFD手法","subitem_subject_scheme":"Other"},{"subitem_subject":"数値流体力学","subitem_subject_scheme":"Other"},{"subitem_subject":"遷移過程","subitem_subject_scheme":"Other"},{"subitem_subject":"Tollmien-Schlichting波","subitem_subject_scheme":"Other"},{"subitem_subject":"前縁","subitem_subject_scheme":"Other"},{"subitem_subject":"超音速風洞","subitem_subject_scheme":"Other"},{"subitem_subject":"SST experimental airplane","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"supersonic transport","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"boundary layer transition","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"transition measurement","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"supersonic flow","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"flight test","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"natural laminar flow wing","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"CFD technique","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"computational fluid dynamics","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"transition process","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"Tollmien Schlichting wave","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"leading edge","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"supersonic wind tunnel","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":"SST実験機に関する幾つかの遷移計測","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"SST実験機に関する幾つかの遷移計測"}]},"item_type_id":"3","owner":"1","path":["1893","1915"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"41361","relation_version_is_last":true,"title":["SST実験機に関する幾つかの遷移計測"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T21:02:14.651954+00:00"}