{"created":"2023-06-20T15:10:02.053876+00:00","id":39630,"links":{},"metadata":{"_buckets":{"deposit":"c5e2e46a-a9f2-4191-ad72-08919c37d553"},"_deposit":{"created_by":1,"id":"39630","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"39630"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00039630","sets":["1887:1893","1896:1898:1913:1916"]},"author_link":["443650","443645","443643","443651","443644","443648","443646","443647","443649","443652"],"item_3_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Measurement of the boundary layer transition point over a 2-D LFC airfoil in transonic flow using liquid crystals"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1995-03","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"11","bibliographicPageStart":"1","bibliographicVolumeNumber":"679","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":"層流制御翼の研究において環境層遷移点を正確に知ることは、その抵抗特性に対する理解を深めるために必要不可欠である。感温液晶による流れの可視化は遷移点測定法として非常に有効な方法であるが、その実際の応用に際しては、幾つかの困難がある。翼表面の温度と用いた感温塗料の発色温度の不一致は、航技研2次元風洞における2次元ハイブリッド層流制御(HLFC)翼の試験において経験した困難の1つである。本報告ではこのような温度の不一致を避ける有効な方法について検討し、集合胴温度の情報が感温液晶の選択において有意義な情報であることを示すとともに、得られた遷移点位置の結果を、ウェーク抵抗の測定結果と関連づけて論じる。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"In the study of laminar-flow-control airfoils, accurate measurement of the boundary layer transition point over the airfoil is quite important to deepen the understanding of its drag characteristics. Flow visualization using temperature-sensing liquid crystals is one of the most useful techniques for detecting the transition point. However, there are some inherent difficulties in its practical applications for wind tunnel testings: mismatching between the airfoil surface temperature and the liquid crystals temperature range is the one encountered in the present blowdown wind tunnel test. With great effort to avoid mismatching, it was used to measure the transition points of a two-dimensional hybrid laminar-flow-control airfoil in high subsonic, high Reynolds number flow at the NAL (National Aerospace Laboratory) 2-D wind tunnel. In the present paper, it is described of the results of the test showing a way to avoid the temperature range mismatching with stagnation temperature in the blowdown wind tunnel test.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0000001000","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-679","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":"航空宇宙技術研究所 空力性能部"},{"subitem_text_value":"航空宇宙技術研究所 空力性能部"},{"subitem_text_value":"航空宇宙技術研究所 空力性能部"},{"subitem_text_value":"航空宇宙技術研究所 空力性能部"},{"subitem_text_value":"航空宇宙技術研究所 空力性能部"}]},"item_3_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Aircraft Aerodynamics Division"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Aircraft Aerodynamics Division"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Aircraft Aerodynamics Division"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Aircraft Aerodynamics Division"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Aircraft Aerodynamics Division"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"野口, 正芳"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"石田, 洋治"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"須谷, 記和"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"佐藤, 衛"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"神田, 宏"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Noguchi, Masayoshi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Ishida, Yoji","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Sudani, Norikazu","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":"naltm00679.pdf","filesize":[{"value":"1.3 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"naltm00679.pdf","url":"https://jaxa.repo.nii.ac.jp/record/39630/files/naltm00679.pdf"},"version_id":"c9858974-69db-4112-8187-b93956573ff1"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"遷音速","subitem_subject_scheme":"Other"},{"subitem_subject":"2次元HLFC翼","subitem_subject_scheme":"Other"},{"subitem_subject":"2次元ハイブリッド層流制御翼","subitem_subject_scheme":"Other"},{"subitem_subject":"境界層遷移点可視化","subitem_subject_scheme":"Other"},{"subitem_subject":"空気力学","subitem_subject_scheme":"Other"},{"subitem_subject":"感温液晶","subitem_subject_scheme":"Other"},{"subitem_subject":"よどみ温度","subitem_subject_scheme":"Other"},{"subitem_subject":"遷移点","subitem_subject_scheme":"Other"},{"subitem_subject":"ウエーク抵抗係数","subitem_subject_scheme":"Other"},{"subitem_subject":"レイノルズ数依存性","subitem_subject_scheme":"Other"},{"subitem_subject":"風洞試験","subitem_subject_scheme":"Other"},{"subitem_subject":"温度測定","subitem_subject_scheme":"Other"},{"subitem_subject":"吸い込み効果","subitem_subject_scheme":"Other"},{"subitem_subject":"亜音速","subitem_subject_scheme":"Other"},{"subitem_subject":"流れの可視化","subitem_subject_scheme":"Other"},{"subitem_subject":"transonic","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"2D HLFC airfoil","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"2D hybrid laminar flow control airfoil","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"boundary layer transition point visualization","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"aerodynamics","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"temperature sensing liquid crystal","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"stagnation temperature","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"transition point","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"wake resistance coefficient","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"Reynolds number dependence","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"wind tunnel test","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"temperature measurement","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"suction effect","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"subsonic speed","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"flow visualization","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 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