{"created":"2023-06-20T15:12:42.110099+00:00","id":42562,"links":{},"metadata":{"_buckets":{"deposit":"5697f5f5-2ce9-4bd3-93d2-61e76be2c88e"},"_deposit":{"created_by":1,"id":"42562","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"42562"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00042562","sets":["1887:1893","1896:1898:1913:1916"]},"author_link":["458998","459005","459004","459010","459002","459006","458997","459008","459007","459009","459000","458999","459001","459003"],"item_3_alternative_title_1":{"attribute_name":"その他のタイトル","attribute_value_mlt":[{"subitem_alternative_title":"第2次遷音速2次元風洞試験"}]},"item_3_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Second 2-dimensional transonic wind tunnel tests"},{"subitem_alternative_title":"Study on high performance/low noise airfoil of helicopter blade"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"2001-10","bibliographicIssueDateType":"Issued"},"bibliographicVolumeNumber":"759","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":"1999年にNAL0.8 x 0.45m高Re数遷音速風洞において、ATICとNALの共同研究として実施した、ATIC翼型の第二次遷音速二次元風洞試験の結果について報告する。本風洞試験では、ATICの第二次設計ステージで新規に設計したAK080E、AK100G、AK120GおよびAK120H翼型と、第一次設計ステージで設計したAK100D翼型の空力データを取得した。上記翼型のうち、AK100G/AK120G翼型は、AK100Dの前縁を変更することによって、M=0.6近辺でのC(sub lmax)の向上を目的として設計したものである。また、AK080E翼型は、AK080A翼型のコンターに修正を加えることによって、C(sub lmax)の向上とC(sub m0)の低減を目的として設計された。AK120H翼型は、AK120G翼型のC(sub m0)を低減することを目的として、AK120G翼型の後縁を修正して再設計されたものである。これらの新しい翼型が、設計時の要求通りの性能を示すことが、本風洞試験において確認された。また、NAL 0.8 x 0.45m高Re数遷音速風洞は、1995-1997年にかけて改修が実施されており、改修前に行われた第一次遷音速二次元風洞試験でも供試体として採用されたAK100D翼型を用いて、風洞改修の影響を評価した。AK100D翼型は、改修前後でほぼ同等の空力特性を示しており、風洞の改修が翼型の空力特性に悪影響を与えていないものと考えられるが、風洞改修の影響を確認するためには、更に詳細な検討が必要である。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"This report shows the results of the second two dimensional transonic wind tunnel testing for new ATIC airfoils. This test was the result of cooperative work between ATIC and NAL (National Aerospace Laboratory of Japan) and was conducted at NAL 0.8 m x 0.45 m High Re. Number Transonic Wind Tunnel in 1999. The new airfoils, AK080E, AK100G, AK120G and AK120H, were designed at the second stage of ATIC airfoil research. AK100G/AK120G were obtained by modifying AK100D, which was designed at the first stage, in order to achieve high C(sub lmax) about March number 0.6. AK080E was made to accomplish high C(sub lmax) and low C(sub m0) by adding the contour change to AK080A, which was designed at the same stage as AK100D. And AK120H was redesigned in order to decrease the C(sub m0) of AK 120G. In this wind tunnel testing, the effect of the improvements of these new airfoils were confirmed. During this test campaign, AK100D was also tested again in order to evaluate the influence of the wind tunnel modification, because NAL 0.8 m x 0.45 m High Re. Number Transonic Wind Tunnel was modified between the first test and this test campaign. AK100D shows the almost same results before and after the modification, and the modification of the wind tunnel seems to have no bad effect on the airfoil aerodynamic characteristics. To confirm the influence of the wind tunnel modification clearly, a more detailed investigation for the characteristic of the wind tunnel may be needed.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0032830000","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-759","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 液体科学研究センター"},{"subitem_text_value":"航空宇宙技術研究所 風洞技術開発センター"},{"subitem_text_value":"航空宇宙技術研究所 風洞技術開発センター"},{"subitem_text_value":"航空宇宙技術研究所 風洞技術開発センター"}]},"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 Fluid Science Research Center"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Wind Tunnel Technology Center"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Wind Tunnel Technology Center"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Wind Tunnel Technology Center"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"辻内, 智郁"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"土橋, 昭彦"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"稲垣, 健次郎"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"斎藤, 茂"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"佐藤, 衛"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"神田, 宏"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"戸田, 亘洋"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Tsujiuchi, Tomoka","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Tsuchihashi, Akihiko","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Inagaki, Kenjiro","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Saito, Shigeru","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Sato, Mamoru","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Kanda, Hiroshi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Toda, Nobuhiro","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":"2020-01-28"}],"displaytype":"detail","filename":"naltm0000759.pdf","filesize":[{"value":"1.0 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"naltm0000759.pdf","url":"https://jaxa.repo.nii.ac.jp/record/42562/files/naltm0000759.pdf"},"version_id":"9c04c606-de30-4881-8d9e-2f90d6df5ef3"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"ヘリコプタブレード","subitem_subject_scheme":"Other"},{"subitem_subject":"高性能","subitem_subject_scheme":"Other"},{"subitem_subject":"低騒音","subitem_subject_scheme":"Other"},{"subitem_subject":"2次元風洞試験","subitem_subject_scheme":"Other"},{"subitem_subject":"遷音速風洞","subitem_subject_scheme":"Other"},{"subitem_subject":"揚力係数","subitem_subject_scheme":"Other"},{"subitem_subject":"圧力係数","subitem_subject_scheme":"Other"},{"subitem_subject":"helicopter blade","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"high performance","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"low noise","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"two dimensional wind tunnel test","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"transonic wind tunnel","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"lift coefficient","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"pressure coefficient","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","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"}]},"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":"42562","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"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T22:23:27.827987+00:00"}