{"created":"2023-06-20T15:11:43.198836+00:00","id":41433,"links":{},"metadata":{"_buckets":{"deposit":"596e540a-c5d4-4186-934f-3e1e83d12ba3"},"_deposit":{"created_by":1,"id":"41433","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"41433"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00041433","sets":["1887:1893","1896:1898:1913:1915"]},"author_link":["490013","490014","490012","490015"],"item_3_alternative_title_1":{"attribute_name":"その他のタイトル","attribute_value_mlt":[{"subitem_alternative_title":"SSTの翼・ナセル形状の翼捩れに対する数値最適化の適用"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"2000-12","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"132","bibliographicPageStart":"131","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":"航空機の設計では、風洞試験やCFD(計算流体力学)法および他の評価法により、様々な機体形状の特性を評価することが必要である。その際、多数の設計パラメータを扱うため、多くの時間がかかる。一方、数値アルゴリズムや計算機のハードウエアの改良により、形状の自動最適化が可能になってきた。そこで、数値最適化法を用いて、揚力係数を一定に保ちながら揚抗比を最大にするように、SSTの翼・ナセル形状機体の翼捩じり分布を決定した。揚抗比を上げるためには、翼・ナセル干渉による抗力を少なくすることが重要である。折曲がり矢羽根翼と2つの2次元的空気取入れ口のある航空機を解析した。始めの翼捩れは0度である。表面翼圧力分布を始めの形状と最適化したとき比較した。最適化した場合、下表面とナセルの間の干渉が減少し、最適化した抗力係数は始めのものより低かった。逐次2次プログラミング法、修正可能方向アルゴリズムおよびジェネティック・アルゴリズムの3つの最適化法について同じ結果が得られた。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"In the process of designing an aircraft, it is necessary to evaluate the characteristics of various configurations with the wind tunnel testing, CFD (Computational Fluid Dynamics) methods and other estimation methods. Taking such process, it takes much time because many design parameters must be taken into consideration. On the other hand, improvement in the numerical algorithms and the computer hardware has made it possible to design an optimized configuration automatically. Then, applying the numerical optimization method, the wing twist distribution of SST wing-nacelle configuration was determined under the condition of maximizing the lift to drag ratio with a constant lift coefficient. In order to improve the lift to drag ratio it is important to reduce the drag due to the wing-nacelle interference. The aircraft with a cranked arrow wing and two nacelles that have two-dimensional intakes was analyzed. Initial wing twist was 0 deg. Surface pressure distributions were compared between initial configuration and the optimized one. In the optimized one, the interference between the lower surface and the nacelle was reduced, and the drag coefficient of the optimized one is lower than that of the initial one. The same results were obtained for three optimization methods of sequential quadratic programming method, modified feasible directions algorithm, and genetic algorithm.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0028638017","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":"富士重工業 航空宇宙事業本部　空力研究課"},{"subitem_text_value":"富士重工業 航空宇宙事業本部　空力研究課"}]},"item_3_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"Fuji Heavy Industries Ltd Aerodynamics Research Section, Aerospace Division"},{"subitem_text_language":"en","subitem_text_value":"Fuji Heavy Industries Ltd Aerodynamics Research Section, Aerospace Division"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"山崎, 哲夫"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"斎藤, 充"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Yamazaki, Tetsuo","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Saito, Mitsuru","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":"nalsp0049017.pdf","filesize":[{"value":"183.2 kB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"nalsp0049017.pdf","url":"https://jaxa.repo.nii.ac.jp/record/41433/files/nalsp0049017.pdf"},"version_id":"15df9db3-c621-4dda-9ed7-be666018b373"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"SST","subitem_subject_scheme":"Other"},{"subitem_subject":"超音速輸送機","subitem_subject_scheme":"Other"},{"subitem_subject":"翼・ナセル形状","subitem_subject_scheme":"Other"},{"subitem_subject":"翼捩れ","subitem_subject_scheme":"Other"},{"subitem_subject":"CFD","subitem_subject_scheme":"Other"},{"subitem_subject":"計算流体力学","subitem_subject_scheme":"Other"},{"subitem_subject":"数値最適化法","subitem_subject_scheme":"Other"},{"subitem_subject":"表面翼圧力分布","subitem_subject_scheme":"Other"},{"subitem_subject":"翼・ナセル干渉","subitem_subject_scheme":"Other"},{"subitem_subject":"SST","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"supersonic transport","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"wing nacelle configuration","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"wing twist","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"CFD","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"computational fluid dynamics","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"numerical optimization method","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"surface pressure distribution","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"wing nacelle interference","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":"An application of numerical optimization to a wing twist of SST wing-nacelle configuration","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"An application of numerical optimization to a wing twist of SST wing-nacelle configuration","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":"41433","relation_version_is_last":true,"title":["An application of numerical optimization to a wing twist of SST wing-nacelle configuration"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T21:00:20.446944+00:00"}