{"created":"2023-06-20T15:12:34.039967+00:00","id":42421,"links":{},"metadata":{"_buckets":{"deposit":"54c0e7d9-bb03-4bea-b989-c34c8d59fa34"},"_deposit":{"created_by":1,"id":"42421","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"42421"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00042421","sets":["1887:1893","1896:1898:1913:1917"]},"author_link":["458297","458298"],"item_3_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Minimization of wave drag due to thickness with constraints on constant volume and maximum thickness position"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"2001-07","bibliographicIssueDateType":"Issued"},"bibliographicVolumeNumber":"1426","bibliographic_titles":[{"bibliographic_title":"航空宇宙技術研究所報告"},{"bibliographic_title":"Technical Report of National Aerospace Laboratory","bibliographic_titleLang":"en"}]}]},"item_3_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"体積と最大厚み位置を指定した時の、厚みによる造波抵抗を最小にする、最適厚み分布を設計する数値計算法を開発した。本方法は線形超音速理論に基づいており、体積一定の条件下での最適厚み分布を求める河崎の方法(文献10)を拡張したものである。新しい拘束条件である最大厚み位置は空力的、構造的の両観点から重要であり、近年注目されている全翼機の設計では必要不可欠である。この拘束条件のついかにより設計可能の範囲は著しく広がり、事実多くの興味ある厚み分布の族が得られている。計算例としてデルタ翼、ゴチック翼、アロー翼の各翼平面形に本計算法を適用し、本設計法の有用性を確かめた。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"A numerical method has been developed for designing minimum-drag supersonic wing thickness with constraints on total volume and wing's maximum thickness position. This method is based on the linearized supersonic theory and is an extension of Kawasaki's method (ref.10) which deals only with total volume constraint. The maximum thickness position of the wing, a new constraint condition, is important information from both aerodynamic and structural points of view. The addition of the constraint has considerably extended the design possibility and has actually produced many interesting optimum thickness families. Numerical examples are given for delta, gothic and arrow wings, which confirm the usefulness of present design method.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0032240000","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 TR-1426","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":"0389-4010","subitem_source_identifier_type":"ISSN"}]},"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 風洞技術開発センター"}]},"item_3_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Wind Tunnel Technology Center"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"石田, 洋治"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Ishida, Yoji","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":"2020-01-28"}],"displaytype":"detail","filename":"naltr0001426.pdf","filesize":[{"value":"1.1 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"naltr0001426.pdf","url":"https://jaxa.repo.nii.ac.jp/record/42421/files/naltr0001426.pdf"},"version_id":"6dc45498-f2ca-424a-9471-c7f682284ec6"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"空力学","subitem_subject_scheme":"Other"},{"subitem_subject":"波抵抗","subitem_subject_scheme":"Other"},{"subitem_subject":"超音速流","subitem_subject_scheme":"Other"},{"subitem_subject":"翼","subitem_subject_scheme":"Other"},{"subitem_subject":"設計解析","subitem_subject_scheme":"Other"},{"subitem_subject":"最適化","subitem_subject_scheme":"Other"},{"subitem_subject":"数値解析","subitem_subject_scheme":"Other"},{"subitem_subject":"体積一定","subitem_subject_scheme":"Other"},{"subitem_subject":"aerodynamics","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"wave drag","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"supersonic flow","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"wing","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"design analysis","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"optimization","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"numerical analysis","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"constant volume","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":"体積と最大厚み位置を与えた時の厚みによる造波抵抗の最小化","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"体積と最大厚み位置を与えた時の厚みによる造波抵抗の最小化"}]},"item_type_id":"3","owner":"1","path":["1893","1917"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"42421","relation_version_is_last":true,"title":["体積と最大厚み位置を与えた時の厚みによる造波抵抗の最小化"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T22:23:41.340219+00:00"}