{"created":"2023-06-20T15:08:17.319420+00:00","id":37699,"links":{},"metadata":{"_buckets":{"deposit":"23c9ee7f-768c-48c1-8ddf-b9cf69c0f438"},"_deposit":{"created_by":1,"id":"37699","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"37699"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00037699","sets":["1887:1891","1896:1898:1913:1915"]},"author_link":["482566","482567","482565","482564"],"item_5_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Numerical analysis of supersonic transport wings"}]},"item_5_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1992-12","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"74","bibliographicPageStart":"69","bibliographicVolumeNumber":"19","bibliographic_titles":[{"bibliographic_title":"航空宇宙技術研究所特別資料: 第10回航空機計算空気力学シンポジウム論文集"},{"bibliographic_title":"Special Publication of National Aerospace Laboratory: Proceedings of the NAL symposium on aircraft computational aerodynamics","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":"航空宇宙技術研究所 10-12 Jun. 1992 東京 日本","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":"National Aerospace Laboratory 10-12 Jun. 1992 Tokyo Japan","subitem_description_type":"Other"}]},"item_5_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"超音速輸送機用主翼の数値解析を行った。翼をワープさせることによる抵抗減少は、超音速巡航条件で0.0006〜0.0010である。オイラー方程式解法を用いた場合の抵抗減少は、線形解法を用いた場合のそれよりも少ないことが判明したが、それは超音速領域における流れのメカニズムが本質的に非線形であることによる。最後に、超音速巡航条件では、クランクアロー翼をもつ翼胴形状が、デルタ翼やオジー翼をもつそれに比べて良い揚抗比をもつことが示された。","subitem_description_type":"Abstract"}]},"item_5_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"Numerical analysis of supersonic transport wings was carried out. The drag reduction obtained by warped wing design technique is from 0.0006 to 0.0010 in supersonic cruise condition. It is also clarified that the drag reduction by use of Euler analysis is less than that by the linear method, because the flow mechanism in supersonic region is essentially non-linear. Finally it is shown that cranked arrow wing-body configuration has the best lift to drag ratio in supersonic cruise condition in comparison with delta or ogee wing-body configuration.","subitem_description_type":"Other"}]},"item_5_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0004168013","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-19","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":"富士重工業"},{"subitem_text_value":"日本航空機開発協会"}]},"item_5_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"Fuji Heavy Industries Ltd"},{"subitem_text_language":"en","subitem_text_value":"Japan Aircraft Development Corporation"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"山崎, 哲夫"}],"nameIdentifiers":[{"nameIdentifier":"482564","nameIdentifierScheme":"WEKO"}]},{"creatorNames":[{"creatorName":"内田, 隆志"}],"nameIdentifiers":[{"nameIdentifier":"482565","nameIdentifierScheme":"WEKO"}]},{"creatorNames":[{"creatorName":"Yamazaki, Tetsuo","creatorNameLang":"en"}],"nameIdentifiers":[{"nameIdentifier":"482566","nameIdentifierScheme":"WEKO"}]},{"creatorNames":[{"creatorName":"Uchida, Takashi","creatorNameLang":"en"}],"nameIdentifiers":[{"nameIdentifier":"482567","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":"nalsp0019013.pdf","filesize":[{"value":"274.4 kB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"nalsp0019013.pdf","url":"https://jaxa.repo.nii.ac.jp/record/37699/files/nalsp0019013.pdf"},"version_id":"f6b8642e-4217-4aa9-a38b-b0fafc40fba4"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"超音速輸送機","subitem_subject_scheme":"Other"},{"subitem_subject":"主翼設計","subitem_subject_scheme":"Other"},{"subitem_subject":"主翼空力特性","subitem_subject_scheme":"Other"},{"subitem_subject":"超音速翼胴結合体","subitem_subject_scheme":"Other"},{"subitem_subject":"デルタ翼","subitem_subject_scheme":"Other"},{"subitem_subject":"オジー翼","subitem_subject_scheme":"Other"},{"subitem_subject":"クランクアロー翼","subitem_subject_scheme":"Other"},{"subitem_subject":"主翼ワープ","subitem_subject_scheme":"Other"},{"subitem_subject":"主翼形状","subitem_subject_scheme":"Other"},{"subitem_subject":"パラメトリックスタディ","subitem_subject_scheme":"Other"},{"subitem_subject":"超音速パネル法","subitem_subject_scheme":"Other"},{"subitem_subject":"オイラー方程式","subitem_subject_scheme":"Other"},{"subitem_subject":"超音速非線形効果","subitem_subject_scheme":"Other"},{"subitem_subject":"超音速揚抗比","subitem_subject_scheme":"Other"},{"subitem_subject":"SST","subitem_subject_scheme":"Other"},{"subitem_subject":"supersonic transport","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"wing design","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"wing characteristic","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"supersonic wing body combination","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"delta wing","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"ogee wing","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"cranked arrow wing","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"wing warp","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"wing geometry","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"parametric study","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"supersonic panel method","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"Euler equation","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"supersonic nonlinear effect","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"supersonic lift to drag ratio","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"SST","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":"超音速輸送機主翼形状の数値解析","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"超音速輸送機主翼形状の数値解析"}]},"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":"37699","relation_version_is_last":true,"title":["超音速輸送機主翼形状の数値解析"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T21:14:40.139139+00:00"}