{"created":"2023-06-20T15:07:49.942715+00:00","id":37197,"links":{},"metadata":{"_buckets":{"deposit":"99e6f171-a1d1-4809-9ed2-f4d5fd09188f"},"_deposit":{"created_by":1,"id":"37197","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"37197"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00037197","sets":["1887:1891","1896:1898:1913:1915"]},"author_link":["479492","479493"],"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 a delta wing at low speed"}]},"item_5_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1998-01","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"185","bibliographicPageStart":"179","bibliographicVolumeNumber":"38","bibliographic_titles":[{"bibliographic_title":"航空宇宙技術研究所特別資料"},{"bibliographic_title":"Special Publication of National Aerospace Laboratory","bibliographic_titleLang":"en"}]}]},"item_5_description_14":{"attribute_name":"会議概要（会議名, 開催地, 会期, 主催者等）","attribute_value_mlt":[{"subitem_description":"22-23 May 1997 (58th). 27-28 Nov. 1997 (59th)","subitem_description_type":"Other"}]},"item_5_description_15":{"attribute_name":"会議概要（会議名, 開催地, 会期, 主催者等）（英）","attribute_value_mlt":[{"subitem_description":"22-23 May 1997 (58th). 27-28 Nov. 1997 (59th)","subitem_description_type":"Other"}]},"item_5_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"感圧塗料は主に無風状態と通風状態の間の圧力変化が大きく、画像のS/N比が大きい遷音速、超音速の風洞試験で従来用いられてきた。本実験では測定部への光学的アクセスが比較的容易な低速風洞試験へ感圧塗料の適用領域を拡大することを目的とし、受光量分解能の高いデジタルCCDカメラを使用するとともに、各種画像処理を行うことによって低速におけるS/N比の低下を克服し、風速35m/sにおいて前縁剥離渦、Vortex Breakdownといった大迎角デルタ翼に特徴的な流れ場を圧力場として定量的に可視化した。","subitem_description_type":"Abstract"}]},"item_5_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"Pressure sensitive paints have been applied mainly to the test in transonic and supersonic wind tunnel in which pressure difference between calm and ventilated condition is large and the S/N ration of images is large. This experiment aims to expand applicable ranges of pressure sensitive paints to the test in low-speed wind tunnel where optically access to measuring parts is relatively easier. For achieving this aim, various kinds of image processing were applied to overcome a lowering of S/N ratio in low-speed region, as well as a digital CCD camera having high actinometric resolution was employed. Further characteristic flow fields of delta wing with high elevation angle, such as leading edge separation vortex or vortex breakdown, were quantitatively visualized as a pressure field at the wind speed of 35 m/s.","subitem_description_type":"Other"}]},"item_5_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0001434015","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: NAL SP-38","subitem_description_type":"Other"}]},"item_5_publisher_8":{"attribute_name":"出版者","attribute_value_mlt":[{"subitem_publisher":"航空宇宙技術研究所"}]},"item_5_publisher_9":{"attribute_name":"出版者（英）","attribute_value_mlt":[{"subitem_publisher":"National Aerospace Laboratory (NAL)"}]},"item_5_source_id_21":{"attribute_name":"ISSN","attribute_value_mlt":[{"subitem_source_identifier":"0289-260X","subitem_source_identifier_type":"ISSN"}]},"item_5_source_id_24":{"attribute_name":"書誌レコードID","attribute_value_mlt":[{"subitem_source_identifier":"AN10097345","subitem_source_identifier_type":"NCID"}]},"item_5_text_6":{"attribute_name":"著者所属","attribute_value_mlt":[{"subitem_text_value":"航空宇宙技術研究所"}]},"item_5_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"真保, 雄一"}],"nameIdentifiers":[{"nameIdentifier":"479492","nameIdentifierScheme":"WEKO"}]},{"creatorNames":[{"creatorName":"Shinbo, Yuichi","creatorNameLang":"en"}],"nameIdentifiers":[{"nameIdentifier":"479493","nameIdentifierScheme":"WEKO"}]}]},"item_files":{"attribute_name":"ファイル情報","attribute_type":"file","attribute_value_mlt":[{"accessrole":"open_date","date":[{"dateType":"Available","dateValue":"2020-02-10"}],"displaytype":"detail","filename":"nalsp0038015.pdf","filesize":[{"value":"1.8 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"nalsp0038015.pdf","url":"https://jaxa.repo.nii.ac.jp/record/37197/files/nalsp0038015.pdf"},"version_id":"adf7661b-855c-46fd-aec6-73f8991adbc2"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"感圧塗料","subitem_subject_scheme":"Other"},{"subitem_subject":"デルタ翼","subitem_subject_scheme":"Other"},{"subitem_subject":"低速風洞試験","subitem_subject_scheme":"Other"},{"subitem_subject":"SN比","subitem_subject_scheme":"Other"},{"subitem_subject":"デジタルCCDカメラ","subitem_subject_scheme":"Other"},{"subitem_subject":"画像処理","subitem_subject_scheme":"Other"},{"subitem_subject":"流れ場","subitem_subject_scheme":"Other"},{"subitem_subject":"圧力場","subitem_subject_scheme":"Other"},{"subitem_subject":"渦崩壊","subitem_subject_scheme":"Other"},{"subitem_subject":"前縁剥離渦","subitem_subject_scheme":"Other"},{"subitem_subject":"pressure sensitive paint","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"delta wing","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"low speed wind tunnel test","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"SN ratio","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"digital CCD camera","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"image processing","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"flow field","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"pressure field","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"vortex breakdown","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"leading edge separation vortex","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 paper","resourceuri":"http://purl.org/coar/resource_type/c_5794"}]},"item_title":"感圧塗料を用いたデルタ翼の低速風洞試験","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"感圧塗料を用いたデルタ翼の低速風洞試験"}]},"item_type_id":"5","owner":"1","path":["1891","1915"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"37197","relation_version_is_last":true,"title":["感圧塗料を用いたデルタ翼の低速風洞試験"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T21:23:39.176926+00:00"}