{"created":"2023-06-20T15:14:14.556375+00:00","id":44223,"links":{},"metadata":{"_buckets":{"deposit":"c9c5f7f8-4abf-416c-87df-c47c0108d0f0"},"_deposit":{"created_by":1,"id":"44223","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"44223"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00044223","sets":["1887:1893","1896:1898:1913:1916"]},"author_link":["468438","468437","468435","468439","468436","468440"],"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1991-09","bibliographicIssueDateType":"Issued"},"bibliographicPageStart":"72","bibliographicVolumeNumber":"640T","bibliographic_titles":[{},{"bibliographic_title":"Technical Memorandum of National Aerospace Laboratory","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二次元風洞の側壁境界層の影響を評価する目的で遷音速域においてNACA0012翼型に関する実験を行った。測定項目は翼表面圧力分布測定,後流トラバースによる抵抗測定の二項目である。マッハ数は約0.65から0.8,迎角は-2°から2°,翼弦長を基準とするレイノズル数は7×106から40×106の範囲で試験を行った。本実験結果に側壁干渉によるマッハ数修正を施し,修正法に検討を加えるとともに,さらに翼弦長の異なる模型についても実験を行いアスペクト比の変化に対する本修正法の適用性の確認も行った。本報告では他風洞及びCFDとの比較研究のための資料として修正前及び修正後の結果を併せて紹介する。本報告は、航空宇宙技術研究所報告TR-1109Tを補足するためのデータ集である。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"An experimental study on NACA0012 airfoils at transonic speeds has been conducted in order to acquire aerodynamic data for evaluating sidewall boundary-layer effects. Measurements primarily consisted of static pressure on the airfoil and drag force coefficients determined using the wake rake. The tests were performed at free-stream Mach numbers from approximately 0.65 to 0.8, at angles of attack from -2.00 to 2.00, and at Reynolds numbers (based on airfoil chord) from 7*106 to 40 * 106. Mach number corrections for sidewall boundary-layer effects were made, and tests were subsequently performed on two different chord airfoils to confirm the applicability of the correction to different airfoil aspect ratios. This is a supplementary report and presents both uncorrected and corrected data which enables comparative studies to be conducted using computational fluid dynamics and other wind tunnel experimental results.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: NALTM0640T000","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 TM-640T","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":"0452-2982","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":"AN00314334","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空力性能部"},{"subitem_text_value":"航空宇宙技術研究所空力性能部"},{"subitem_text_value":"航空宇宙技術研究所空力性能部"},{"subitem_text_value":"航空宇宙技術研究所空力性能部"},{"subitem_text_value":"航空宇宙技術研究所空力性能部"},{"subitem_text_value":"航空宇宙技術研究所空力性能部"}]},"item_3_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"Aircraft Aerodynamics Division"},{"subitem_text_language":"en","subitem_text_value":"Aircraft Aerodynamics Division"},{"subitem_text_language":"en","subitem_text_value":"Aircraft Aerodynamics Division"},{"subitem_text_language":"en","subitem_text_value":"Aircraft Aerodynamics Division"},{"subitem_text_language":"en","subitem_text_value":"Aircraft Aerodynamics Division"},{"subitem_text_language":"en","subitem_text_value":"Aircraft Aerodynamics Division"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"SUDANI, Norikazu","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"KANDA, Hiroshi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"SATO, Mamoru","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"BABA, Shigeo","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"MIWA, Hitoshi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"MATSUNO, Kenichi","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":"2020-01-29"}],"displaytype":"detail","filename":"naltm0640t.pdf","filesize":[{"value":"3.6 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"naltm0640t.pdf","url":"https://jaxa.repo.nii.ac.jp/record/44223/files/naltm0640t.pdf"},"version_id":"13b27da6-f8bb-49ba-9b1f-4928f698916c"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"Airfoil Data;  Transonic Flow;  NACA0012;  Wind Tunnel Test;  Sidewall Correction","subitem_subject_language":"en","subitem_subject_scheme":"Other"}]},"item_language":{"attribute_name":"言語","attribute_value_mlt":[{"subitem_language":"eng"}]},"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":"NACA0012 Airfoil Data Corrected for Sidewall Boundary-layer Effects in the NAL Two-Dimensional Transonic Wind Tunnel","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"NACA0012 Airfoil Data Corrected for Sidewall Boundary-layer Effects in the NAL Two-Dimensional Transonic Wind Tunnel","subitem_title_language":"en"}]},"item_type_id":"3","owner":"1","path":["1893","1916"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"44223","relation_version_is_last":true,"title":["NACA0012 Airfoil Data Corrected for Sidewall Boundary-layer Effects in the NAL Two-Dimensional Transonic Wind Tunnel"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T22:00:40.453634+00:00"}