{"created":"2023-06-20T15:11:43.754729+00:00","id":41445,"links":{},"metadata":{"_buckets":{"deposit":"61027eac-36c6-4f92-9f1f-f358e7e63cc4"},"_deposit":{"created_by":1,"id":"41445","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"41445"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00041445","sets":["1887:1893","1896:1898:1913:1915"]},"author_link":["490060","490061"],"item_3_alternative_title_1":{"attribute_name":"その他のタイトル","attribute_value_mlt":[{"subitem_alternative_title":"自然層流超音速航空機翼の空力設計"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"2000-12","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"209","bibliographicPageStart":"203","bibliographicVolumeNumber":"49T","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_3_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":"航空宇宙技術研究所 17-19 Jan. 2000 東京 日本","subitem_description_type":"Other"}]},"item_3_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":"National Aerospace Laboratory 17-19 Jan. 2000 Tokyo Japan","subitem_description_type":"Other"}]},"item_3_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"超音速航空機の翼に対する自然層流(NLF)の空力設計を3次元CFD(計算流体力学)および境界層安定解析を用い行った。NLF翼設計に対して2つの主題がある。1つは航空宇宙技術研究所(NAL)の小型無人超音速実験機のL/D(揚力/抗力)比を改善することである。全抗力のほとんど半分に達するこの翼部の表面摩擦抗力を減少するため特に設計を行った。この目的のために3次元CFDソルバおよび3次元層流境界安定解析と2次元逆設計法を用い出来るだけ層流を維持するように設計した。もう1つは翼長方向の圧力分布を考慮してクロス流れの不安定性による遷移を遅らせるように簡単な後退翼を設計した。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"Aerodynamic design of Natural Laminar Flow (NLF) for supersonic aircraft wings was conducted by using 3-D CFD analysis and boundary layer stability analysis. There are two main subjects for NLF wing design. One is that the wing of the sub-scaled unmanned supersonic experimental aircraft of National Aerospace Laboratory (NAL) was designed to improve the L/D (Lift/Drag) ratio. The wing sections were designed especially to reduce skin friction drag which amounts to nearly half of the total drag. For this purpose, we designed the wing sections to remain laminar flow as far as possible using 3-D CFD solver and 3-D laminar boundary layer stability analysis code and 2-D inverse design method. The other is that the simple sweep-back wing was designed to delay a transition due to cross flow instability in consideration of spanwise pressure distribution.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0028638029","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 SP-49T","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":"0289-260X","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":"AN10097345","subitem_source_identifier_type":"NCID"}]},"item_3_text_6":{"attribute_name":"著者所属","attribute_value_mlt":[{"subitem_text_value":"川崎重工業 岐阜技術研究所"}]},"item_3_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"Kawasaki Heavy Industries LTD Gifu Technology Institute"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"生越, 博景"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Ogoshi, Hirokage","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":"2020-02-10"}],"displaytype":"detail","filename":"nalsp0049029.pdf","filesize":[{"value":"1.4 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"nalsp0049029.pdf","url":"https://jaxa.repo.nii.ac.jp/record/41445/files/nalsp0049029.pdf"},"version_id":"c550f757-d1f9-46a3-9a10-6b762a7c762b"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"空力設計","subitem_subject_scheme":"Other"},{"subitem_subject":"超音速航空機翼","subitem_subject_scheme":"Other"},{"subitem_subject":"NLF","subitem_subject_scheme":"Other"},{"subitem_subject":"自然層流","subitem_subject_scheme":"Other"},{"subitem_subject":"境界層安定解析","subitem_subject_scheme":"Other"},{"subitem_subject":"超音速実験機","subitem_subject_scheme":"Other"},{"subitem_subject":"L/D比","subitem_subject_scheme":"Other"},{"subitem_subject":"揚力対抗力比","subitem_subject_scheme":"Other"},{"subitem_subject":"逆設計法","subitem_subject_scheme":"Other"},{"subitem_subject":"aerodynamic design","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"supersonic aircraft wing","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"NLF","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"natural laminar flow","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"boundary layer stability analysis","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"supersonic experimental aircraft","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"L to D ratio","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"lift to drag ratio","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"inverse design method","subitem_subject_language":"en","subitem_subject_scheme":"Other"}]},"item_language":{"attribute_name":"言語","attribute_value_mlt":[{"subitem_language":"eng"}]},"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":"Aerodynamic design of natural laminar flow supersonic aircraft wings","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"Aerodynamic design of natural laminar flow supersonic aircraft wings","subitem_title_language":"en"}]},"item_type_id":"3","owner":"1","path":["1893","1915"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"41445","relation_version_is_last":true,"title":["Aerodynamic design of natural laminar flow supersonic aircraft wings"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T21:00:04.902596+00:00"}