{"created":"2023-06-20T15:14:18.218237+00:00","id":44296,"links":{},"metadata":{"_buckets":{"deposit":"7c7699f8-56c3-48a1-8804-5022c935e829"},"_deposit":{"created_by":1,"id":"44296","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"44296"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00044296","sets":["1887:1893","1896:1898:1913:1917"]},"author_link":["468790","468789"],"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1964-01","bibliographicIssueDateType":"Issued"},"bibliographicPageStart":"17","bibliographicVolumeNumber":"57T","bibliographic_titles":[{},{"bibliographic_title":"Technical Report of National Aerospace Laboratory TR-57T","bibliographic_titleLang":"en"}]}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"The aerodynamic derivatives of a biconvex-flat airfoil (thickness ratio of 10 per cent), and double-wedge airfoils (thickness ratios of 10, 15, 20 percent), performing pitching oscillation in supersonic flow at the range of Mach number2-3, were measured and compared with the linearized theory, piston theory and Van Dyke's nonlinear theory which includes the effect of the airfoil thickness. The tested reduced frequency range was 0.01-0.05 and the Reynolds number range was 2.8 by 10(6)-3.6 by10(6) based on the chord length. In spite of the existence of the detached shock wave in front of the leading edge of the biconvex-flat airfoil, all experimental results agree quite well with the nonlinear theory. Schlieren photographs were taken in order to observe the flow field around the airfoils.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: NALTR0057T000","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 TR-57T","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":"0389-4010","subitem_source_identifier_type":"ISSN"}]},"item_3_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"National Aeronautical Laboratory First Aerodynamics Division"},{"subitem_text_language":"en","subitem_text_value":"Nippon Oil Seal Industry Co., Ltd., First Aerodynamics Division, National Aeronautical Laboratory(NAL)"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"ISHII, Takao","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"YANAGIZAWA, Mitsunori","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":"naltr0057t.pdf","filesize":[{"value":"3.4 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"naltr0057t.pdf","url":"https://jaxa.repo.nii.ac.jp/record/44296/files/naltr0057t.pdf"},"version_id":"d1e7cf87-998e-41b1-ad21-27de9ad26eb4"}]},"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":"Measurements of the Aerodynamic Derivatives of an Oscillating Biconvex-Flat Airfoil in Supersonic Flow at Mach Number 2 to 3","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"Measurements of the Aerodynamic Derivatives of an Oscillating Biconvex-Flat Airfoil in Supersonic Flow at Mach Number 2 to 3","subitem_title_language":"en"}]},"item_type_id":"3","owner":"1","path":["1893","1917"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"44296","relation_version_is_last":true,"title":["Measurements of the Aerodynamic Derivatives of an Oscillating Biconvex-Flat Airfoil in Supersonic Flow at Mach Number 2 to 3"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T21:59:23.202502+00:00"}