{"created":"2023-06-20T15:10:43.330021+00:00","id":40297,"links":{},"metadata":{"_buckets":{"deposit":"c43fb9cd-77fb-4101-afb6-b31ec8498dd9"},"_deposit":{"created_by":1,"id":"40297","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"40297"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00040297","sets":["1887:1893","1896:1898:1913:1916"]},"author_link":["447157","447158","447153","447160","447152","447156","447161","447151","447163","447159","447155","447162","447154","447150"],"item_3_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Study on high performance/low noise airfoil of helicopter blade: Two-dimensional transonic wind tunnel tests"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1998-07","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"18","bibliographicPageStart":"1","bibliographicVolumeNumber":"730","bibliographic_titles":[{"bibliographic_title":"航空宇宙技術研究所資料"},{"bibliographic_title":"Technical Memorandum of National Aerospace Laboratory","bibliographic_titleLang":"en"}]}]},"item_3_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"高性能/低騒音ヘリコプタ・ブレード用翼型が新しい概念を用いて提案された。ブレードの翼端付近では8%翼厚、ブレードの翼根付近では10%翼厚を持つ新しい翼型が設計された。この研究においては、現存する翼型に対して、高C(sub lmax)(最大揚力係数)かつ高M(sub dd)(抵抗発散マッハ数)を持つ翼型が空気力学特性に対する設計思想として考えられた。航空宇宙技術研究所にある2次元風洞を用いてそれら新翼型の空気性能を検証するための風洞試験が行われた。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"High performance/low noise airfoils of a helicopter rotor have been proposed based on a new concept. Those new airfoils were designed for the blade tip section (8 percent thickness ratio) and for the blade root section (10 percent thickness ratio). In this study, the aerodynamic performance was set to be higher than C(sub lmax) (maximum lift coefficient), M(sub dd) (resistance divergence Mach number) and L/D (lift drag ratio) of existing airfoils. To verify the aerodynamic performance of the new airfoils, wind tunnel tests were conducted in the two dimensional transonic wind tunnel at NAL.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0001657000","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-730","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":"コミュータヘリコプタ先進技術研究所"},{"subitem_text_value":"コミュータヘリコプタ先進技術研究所"},{"subitem_text_value":"コミュータヘリコプタ先進技術研究所"},{"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"},{"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":"Advanced Technology Institute of Commuter-Helicopter Ltd"},{"subitem_text_language":"en","subitem_text_value":"Advanced Technology Institute of Commuter-Helicopter Ltd"},{"subitem_text_language":"en","subitem_text_value":"Advanced Technology Institute of Commuter-Helicopter Ltd"},{"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":"青木, 誠"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"小曳, 昇"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"山川, 榮一"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"齊藤, 茂"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"重見, 仁"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"佐藤, 衛"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"神田, 宏"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Aoki, Makoto","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Kobiki, Noboru","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Yamakawa, Eiichi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Saito, Shigeru","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Shigemi, Masashi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Sato, Mamoru","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Kanda, Hiroshi","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":"2020-01-27"}],"displaytype":"detail","filename":"naltm0000730.pdf","filesize":[{"value":"1.9 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"naltm0000730.pdf","url":"https://jaxa.repo.nii.ac.jp/record/40297/files/naltm0000730.pdf"},"version_id":"ff82ef72-cf4e-4aca-a2a7-21250e7521f0"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"ヘリコプタ・ブレード揚抗比","subitem_subject_scheme":"Other"},{"subitem_subject":"低騒音翼型","subitem_subject_scheme":"Other"},{"subitem_subject":"遷音速風洞試験","subitem_subject_scheme":"Other"},{"subitem_subject":"2次元風洞試験","subitem_subject_scheme":"Other"},{"subitem_subject":"空力騒音抑制","subitem_subject_scheme":"Other"},{"subitem_subject":"翼型設計","subitem_subject_scheme":"Other"},{"subitem_subject":"アクティブフラップ","subitem_subject_scheme":"Other"},{"subitem_subject":"失速特性","subitem_subject_scheme":"Other"},{"subitem_subject":"高性能翼型","subitem_subject_scheme":"Other"},{"subitem_subject":"helicopter blade","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"low noise airfoil","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"transonic wind tunnel","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"two dimensional wind tunnel","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"aerodynamic noise suppression","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"airfoil design","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"active flap","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"stall characteristic","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"high performance airfoil","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":"高性能/低騒音ヘリコプタ・ブレード用翼型の研究:遷音速二次元風洞試験","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"高性能/低騒音ヘリコプタ・ブレード用翼型の研究:遷音速二次元風洞試験"}]},"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":"40297","relation_version_is_last":true,"title":["高性能/低騒音ヘリコプタ・ブレード用翼型の研究:遷音速二次元風洞試験"],"weko_creator_id":"1","weko_shared_id":1},"updated":"2023-06-20T19:16:11.380343+00:00"}