{"created":"2023-06-20T14:39:47.510068+00:00","id":6587,"links":{},"metadata":{"_buckets":{"deposit":"b886373a-75d6-48eb-a58a-8995e2781cff"},"_deposit":{"created_by":1,"id":"6587","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"6587"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00006587","sets":["1887:1891","9:789:1085:1087"]},"author_link":["33694","33689","33691","33692","33693","33695","33688","33697","33690","33696"],"item_5_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Pressure sensitive paint application to the transonic wind tunnel test of the powered national supersonic experimental transport"}]},"item_5_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"2004-03-25","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"18","bibliographicPageStart":"14","bibliographicVolumeNumber":"JAXA-SP-03-004","bibliographic_titles":[{"bibliographic_title":"宇宙航空研究開発機構特別資料: 第67回　風洞研究会議論文集"},{"bibliographic_title":"JAXA Special Publication: Proceedings of the Wind Tunnel Technology Association 67th Meeting","bibliographic_titleLang":"en"}]}]},"item_5_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"次世代SSTの開発において空力設計上の主要な課題となる機体／推進系の干渉問題の詳細を把握するため、フロースルーナセルの後方に流量調整用のプラグ装置を有する模型を用いて推進系付き小型超音速実験機(ジェット実験機)の風洞試験を航空宇宙技術研究所2m×2m遷音速風洞において実施した。本試験では通常の空気力、圧力の計測に加え、感圧塗料を用いた表面圧力の計測を同時に行うことによってデータ生産性を飛躍的に向上させると共に、フロースルーナセル内の空気流量の減少に伴うナセル抵抗の増加がナセル入口前方に形成される強い圧縮領域によるものであることを明らかにした。本試験で得られたデータはジェット実験機の開発およびにその設計ツールとなるCFDコードの検証に役立てられる予定である。","subitem_description_type":"Abstract"}]},"item_5_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0047429003","subitem_description_type":"Other"}]},"item_5_description_33":{"attribute_name":"レポート番号","attribute_value_mlt":[{"subitem_description":"レポート番号: 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test","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"wind tunnel model","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"supersonic aircraft","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"pressure sensitive paint","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"pressure field","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"CFD","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"flow-through nacelle","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":"conference 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