{"created":"2023-06-20T15:08:04.864661+00:00","id":37469,"links":{},"metadata":{"_buckets":{"deposit":"cfe8a95e-2ad9-4ee0-a7cf-e1cd2bc76353"},"_deposit":{"created_by":1,"id":"37469","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"37469"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00037469","sets":["1887:1891","1896:1898:1913:1915"]},"author_link":["480947","480945","480948","480946"],"item_5_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"An application of numerical optimization to a wing twist of SST wing-nacelle configuration"}]},"item_5_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1999-12","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"240","bibliographicPageStart":"235","bibliographicVolumeNumber":"44","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_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 16-18 Jun. 1999 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 16-18 Jun. 1999 Tokyo Japan","subitem_description_type":"Other"}]},"item_5_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"航空機の開発において基本的形態を決定するためには、初期候補形態と様々な代替形態の各々の特性をCFD(数値流体力学)と風洞試験により推定する。それぞれの性能を比較、評価し、要求性能を満たす最終形態を決定する。これが一般的な設計プロセスである。しかし、この方法では最適形態を得るためにパラメータを種々変更するという膨大な労力を要し、かつ設計者の経験に依存する傾向がある。近年この問題を解くために空力形状への最適化設計の適用が国内外で研究されている。CFDの発達と計算速度の進歩により最適設計が現実的となりつつあり、自動化されたパラメトリックスタディにより設計プロセスに要する時間の短縮が可能である。現実的なSSTの形態としては、エンジンナセルは主翼の下に釣り下げる可能性が高い。従って主翼とナセルおよび胴体間の干渉抗力を低減することが重要である。主翼に関して捻り角や翼の反りおよびナセルの位置は、パラメータとして干渉抗力の低減に影響する。しかし計算簡略化のため捻り角は設計パラメータとして扱った。本研究では一定の揚力係数のもと、抗力係数を低減させるようSST主翼-ナセル形態のねじり角の最適化を行った。最適形態について、ナセル装着位置近傍の主翼のねじりにより抗力係数にして約5カウント低減することができた。","subitem_description_type":"Abstract"}]},"item_5_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"In order to obtain a fundamental configuration in the development of aircraft, characteristics of an initial candidate and various alternative configurations are estimated by CFD (Computational Fluid Dynamics) and wind tunnel tests. Performance of them are compared and evaluated, and a final configuration which satisfies the demand of performance is decided. These are the general process of design. However, it requires a great deal of labor to obtain optimal configurations by parametric study, and this process has a tendency to depend on designer's experiences. Recently, application of optimal design to aerodynamic shapes is carried out all over the world so as to solve these problems. Optimal design is making practicable with the advance of CFD and computational speed, and automatic parametric study makes it possible to reduce the required time to design process. There is every possibility that nacelles for a practical SST will be hanged below wings. It is important to reduce interference drag among wings, nacelles and fuselage. The twist angles, the camber and the position of nacelles for main wings are parameters which affect the reduction of interference drag. However in order to simplify the computation process, twist angles are selected as design parameters. In this study, an optimization of twist angles for SST wing-nacelle configuration was carried out so that the drag coefficient was reduced under a constant lift coefficient. For the optimal configuration, the twist of main wings near the position of nacelle installation brought the reduction of the drag coefficient by about five counts.","subitem_description_type":"Other"}]},"item_5_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0001961036","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-44","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 航空宇宙事業本部"},{"subitem_text_value":"富士重工業 航空宇宙事業本部"}]},"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 Aerospace Division"},{"subitem_text_language":"en","subitem_text_value":"Fuji Heavy Industries Ltd Aerospace Division"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"松田, 昌三"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"若井, 洋"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Matsuda, Masami","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Wakai, Hiroshi","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":"nalsp0044036.pdf","filesize":[{"value":"449.8 kB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"nalsp0044036.pdf","url":"https://jaxa.repo.nii.ac.jp/record/37469/files/nalsp0044036.pdf"},"version_id":"c1991cd7-ec91-49ad-ba14-00e7c68ed968"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"エンジンナセル","subitem_subject_scheme":"Other"},{"subitem_subject":"SST","subitem_subject_scheme":"Other"},{"subitem_subject":"超音速輸送","subitem_subject_scheme":"Other"},{"subitem_subject":"主翼設計","subitem_subject_scheme":"Other"},{"subitem_subject":"最適形状","subitem_subject_scheme":"Other"},{"subitem_subject":"最適化","subitem_subject_scheme":"Other"},{"subitem_subject":"主翼捻り角","subitem_subject_scheme":"Other"},{"subitem_subject":"干渉抗力","subitem_subject_scheme":"Other"},{"subitem_subject":"抗力係数","subitem_subject_scheme":"Other"},{"subitem_subject":"CFD","subitem_subject_scheme":"Other"},{"subitem_subject":"数値流体力学","subitem_subject_scheme":"Other"},{"subitem_subject":"engine nacelle","subitem_subject_language":"en","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 design","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"optimal configuration","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"optimization","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"wing twist angle","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"interference drag","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"drag coefficient","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"}]},"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":"ナセル付きSST主翼の捻り角最適化","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"ナセル付きSST主翼の捻り角最適化"}]},"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":"37469","relation_version_is_last":true,"title":["ナセル付きSST主翼の捻り角最適化"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T21:18:10.564197+00:00"}