{"created":"2023-06-20T14:35:51.713241+00:00","id":2137,"links":{},"metadata":{"_buckets":{"deposit":"b8bb2daa-0adc-4717-85f3-f99899c3051c"},"_deposit":{"created_by":1,"id":"2137","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"2137"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00002137","sets":["1887:1893","9:10:147:162"]},"author_link":["3655","3654","3656","3657"],"item_3_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Transition measurement using hot-film on supersonic experimental airplane NEXST-1"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"2008-02-29","bibliographicIssueDateType":"Issued"},"bibliographicVolumeNumber":"JAXA-RR-07-037","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":"小型超音速実験機(ロケット実験機; NEXST-1: National EXperimental Supersonic Transport-1)の主翼および前胴の境界層遷移を、ホットフィルムを初めとする4種類のセンサーで計測した。小型超音速実験機の設計には、超音速機の抵抗を低減するためワープ主翼やエリアルール胴体などとともに、自然層流翼のコンセプトが世界初の試みとして適用されており、自然層流翼の実験的検証は飛行実験における最重要計測項目の1つに挙げられていた。2005年10月10日、南オーストラリア州ウーメラで実施された飛行実験では、気流乱れの小さい飛行実験条件下で、貴重な境界層遷移のデータを健全に取得することができた。解析の結果、設計点において主翼上面の境界層遷移位置が非設計点と比べ最も後退していることが明らかになり、自然層流効果が確認された。本稿では、ホットフィルムに焦点を絞り、飛行実験で得られたホットフィルム全20チャンネルのデータを詳しく解析して遷移位置を特定した結果を報告する。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"Boundary layer transition on natural laminar flow wing is measured using hot-film and other three kinds of sensors by the flight test of an unmanned and scaled supersonic experimental airplane. The main purpose of the flight test is experimental validation of the natural laminar flow wing designed with the original CFD (Computational Fluid Dynamics)-based inverse design method, which is applied to a supersonic vehicle as the first challenge in the world. Transition location is classified by using newly introduced quantity, called 'transition level', based on objective criteria. The transition location detected experimentally is in good agreement with numerically predicted location, and the natural laminar flow effect is confirmed at the design condition.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0064087000","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-07-037","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 航空プログラムグループ　企画推進室"}]},"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 Program Office, Aviation Program Group"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"徳川, 直子"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"吉田, 憲司"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Tokugawa, Naoko","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Yoshida, Kenji","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":"64087000.pdf","filesize":[{"value":"14.1 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"64087000.pdf","url":"https://jaxa.repo.nii.ac.jp/record/2137/files/64087000.pdf"},"version_id":"16238c5d-2bf8-4172-9170-c9cfe8ce9b56"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"境界層遷移","subitem_subject_scheme":"Other"},{"subitem_subject":"実験機","subitem_subject_scheme":"Other"},{"subitem_subject":"超音速機","subitem_subject_scheme":"Other"},{"subitem_subject":"飛行試験","subitem_subject_scheme":"Other"},{"subitem_subject":"航空機設計","subitem_subject_scheme":"Other"},{"subitem_subject":"自然層流翼","subitem_subject_scheme":"Other"},{"subitem_subject":"風洞試験","subitem_subject_scheme":"Other"},{"subitem_subject":"計算流体力学","subitem_subject_scheme":"Other"},{"subitem_subject":"熱膜流速計","subitem_subject_scheme":"Other"},{"subitem_subject":"流れ計測","subitem_subject_scheme":"Other"},{"subitem_subject":"boundary layer transition","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"research aircraft","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"supersonic aircraft","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"flight test","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"aircraft design","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"natural laminar flow wing","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"wind tunnel test","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"computational fluid dynamics","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"hot-film anemometer","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"flow measurement","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":"ホットフィルムを用いた超音速小型実験機の遷移計測","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"ホットフィルムを用いた超音速小型実験機の遷移計測"}]},"item_type_id":"3","owner":"1","path":["162","1893"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"2137","relation_version_is_last":true,"title":["ホットフィルムを用いた超音速小型実験機の遷移計測"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-21T09:28:01.598710+00:00"}