{"created":"2023-06-20T14:35:51.058700+00:00","id":2127,"links":{},"metadata":{"_buckets":{"deposit":"69472582-07ab-47e4-bdbc-8d9f3e6a1961"},"_deposit":{"created_by":1,"id":"2127","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"2127"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00002127","sets":["1887:1893","9:10:147:152"]},"author_link":["3574","3579","3581","3572","3577","3582","3571","3576","3578","3570","3575","3580","3583","3573"],"item_3_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Mach 5 wind tunnel test of hypersonic airplane"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"2008-02-29","bibliographicIssueDateType":"Issued"},"bibliographicVolumeNumber":"JAXA-RR-07-047","bibliographic_titles":[{"bibliographic_title":"宇宙航空研究開発機構研究開発報告"},{"bibliographic_title":"JAXA Research and Development Report","bibliographic_titleLang":"en"}]}]},"item_3_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"極超音速実験機のマッハ5空力特性を0.5mJAXA極超音速風洞で取得した。機体模型の6分力計測を行うとともに、実験機の飛行環境を摸擬したCFD(Computational Fluid Dynamics)解析を実施した。結果として、迎角に対する空力係数の変化は風洞試験とCFDで概ね一致した。風洞試験においては、機体上面に大規模な剥離域が観察された。風洞試験とCFDにおける空力係数の違いは、剥離域の違いの影響と推測された。エンジンを装着した形状では、法線力係数と軸力係数が上昇した。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"Mach 5 aerodynamic coefficients for a hypersonic experimental airplane are examined at JAXA 0.5 m hypersonic wind tunnel. Six DOF (Degree Of Freedom) forces for the model are measured and evaluated. CFD (Computational Fluid Dynamics) analyses for the same airframe are performed simulating real flight condition for the experimental airplane. As a result, variations of aerodynamic coefficients on angle of attack for both wind tunnel test and CFD analysis are consistent in general. Large separation region is observed on the upper surface of the body at the wind tunnel test. It is presumed that the difference of aerodynamic coefficients has occurred by the difference in flow separation between the wind tunnel test and CFD. Lateral force coefficient and axial force coefficient are raised with engine installed configuration.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0063912000","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: JAXA-RR-07-047","subitem_description_type":"Other"}]},"item_3_publisher_8":{"attribute_name":"出版者","attribute_value_mlt":[{"subitem_publisher":"宇宙航空研究開発機構"}]},"item_3_publisher_9":{"attribute_name":"出版者（英）","attribute_value_mlt":[{"subitem_publisher":"Japan Aerospace Exploration Agency (JAXA)"}]},"item_3_source_id_21":{"attribute_name":"ISSN","attribute_value_mlt":[{"subitem_source_identifier":"1349-1113","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":"AA1192675X","subitem_source_identifier_type":"NCID"}]},"item_3_text_6":{"attribute_name":"著者所属","attribute_value_mlt":[{"subitem_text_value":"宇宙航空研究開発機構 航空プログラムグループ　超音速機チーム"},{"subitem_text_value":"宇宙航空研究開発機構 総合技術研究本部　空気力学研究グループ"},{"subitem_text_value":"宇宙航空研究開発機構 航空プログラムグループ　超音速機チーム"},{"subitem_text_value":"宇宙航空研究開発機構 総合技術研究本部　風洞技術開発センター"},{"subitem_text_value":"宇宙航空研究開発機構 総合技術研究本部　風洞技術開発センター"},{"subitem_text_value":"宇宙航空研究開発機構 総合技術研究本部　風洞技術開発センター"},{"subitem_text_value":"宇宙航空研究開発機構 情報・計算工学センター"}]},"item_3_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"Japan Aerospace Exploration Agency Supersonic Transport Team, Aviation Program Group"},{"subitem_text_language":"en","subitem_text_value":"Japan Aerospace Exploration Agency Aerodynamics Research Group, Institute of Aerospace Technology"},{"subitem_text_language":"en","subitem_text_value":"Japan Aerospace Exploration Agency Supersonic Transport Team, Aviation Program Group"},{"subitem_text_language":"en","subitem_text_value":"Japan Aerospace Exploration Agency Wind Tunnel Technology Center, Institute of Aerospace Technology"},{"subitem_text_language":"en","subitem_text_value":"Japan Aerospace Exploration Agency Wind Tunnel Technology Center, Institute of Aerospace Technology"},{"subitem_text_language":"en","subitem_text_value":"Japan Aerospace Exploration Agency Wind Tunnel Technology Center, Institute of Aerospace Technology"},{"subitem_text_language":"en","subitem_text_value":"Japan Aerospace Exploration Agency JAXA's Engineering Digital Innovation Center"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"田口, 秀之"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"藤田, 和央"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"進藤, 重美"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"津田, 尚一"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"平林, 則明"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"小山, 忠勇"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"伊藤, 良三"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Taguchi, Hideyuki","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Fujita, Kazuhisa","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Shindo, Shigemi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Tsuda, Shoichi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Hirabayashi, Noriaki","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Koyama, Tadao","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Ito, Ryozo","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":"2020-01-15"}],"displaytype":"detail","filename":"63912000.pdf","filesize":[{"value":"1.5 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"63912000.pdf","url":"https://jaxa.repo.nii.ac.jp/record/2127/files/63912000.pdf"},"version_id":"d0f67e82-26fb-4f50-a048-82d49d812653"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"空力係数","subitem_subject_scheme":"Other"},{"subitem_subject":"空力特性","subitem_subject_scheme":"Other"},{"subitem_subject":"極超音速機","subitem_subject_scheme":"Other"},{"subitem_subject":"風洞試験","subitem_subject_scheme":"Other"},{"subitem_subject":"風洞模型","subitem_subject_scheme":"Other"},{"subitem_subject":"計算流体力学","subitem_subject_scheme":"Other"},{"subitem_subject":"迎角","subitem_subject_scheme":"Other"},{"subitem_subject":"マッハ数","subitem_subject_scheme":"Other"},{"subitem_subject":"剥離流","subitem_subject_scheme":"Other"},{"subitem_subject":"境界層剥離","subitem_subject_scheme":"Other"},{"subitem_subject":"エンジン装着形状","subitem_subject_scheme":"Other"},{"subitem_subject":"aerodynamic coefficient","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"aerodynamic characteristic","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"hypersonic aircraft","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"wind tunnel test","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"wind tunnel model","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"computational fluid dynamics","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"angle of attack","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"Mach number","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"separated flow","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"boundary layer separation","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"engine-installed configuration","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":"極超音速機のマッハ5空力特性試験","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"極超音速機のマッハ5空力特性試験"}]},"item_type_id":"3","owner":"1","path":["152","1893"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"2127","relation_version_is_last":true,"title":["極超音速機のマッハ5空力特性試験"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-21T09:28:11.122805+00:00"}