{"created":"2023-06-20T15:07:48.390773+00:00","id":37166,"links":{},"metadata":{"_buckets":{"deposit":"274324c8-9650-45b5-bd93-8fcea2b1d915"},"_deposit":{"created_by":1,"id":"37166","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"37166"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00037166","sets":["1887:1891","1896:1898:1913:1915"]},"author_link":["479256","479257","479253","479252","479258","479259","479255","479254"],"item_5_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Wing planform design using multidisciplinary optimization"}]},"item_5_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1998-02","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"252","bibliographicPageStart":"247","bibliographicVolumeNumber":"37","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 12-13 Jun. 1997 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 12-13 Jun. 1997 Tokyo Japan","subitem_description_type":"Other"}]},"item_5_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"本研究では、空力性能、翼重量および燃料重量などの翼平面形状の最適化に関して、3つの目的関数ならびに2つの制限を考察した。CFD(数値流体力学)により空力性能を評価した。翼重量および燃料タンク容積を経験式により推定した。問題を単純化するため、前縁後退角および中央と翼端での2つの翼弦長のみを設計変数として用いた。翼前縁を直線とした。このようにして、後縁キンクを伴うテーパ翼の設計を試みた。ここでは最適化にGA(遺伝的アルゴリズム)を採用した。GAでは大域的最適化を見出せるので、従来の勾配法よりも良い性能設計が期待される。GAの大きな欠点は多数の関数評価を要することである。そこで、オイラーまたはナビエ・ストークスソルバに代えて、効率の良い完全ポテンシャル方程式に基づくFLO-22コードを用いた。NAL(航空宇宙技術研究所)のNWT(数値風洞)でGA個体集団の評価を並列処理した。翼平面形状最適化問題を典型的亜音速および遷音速航空機として考察した。設計結果は、初期形状を最適化するこの方法の実現可能性を示した。","subitem_description_type":"Abstract"}]},"item_5_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"In this work, three objectives and two constraints are considered for wing planform optimization: aerodynamic performance, wing weight and fuel weight. Aerodynamic performance is evaluated by Computational Fluid Dynamics (CFD). Wing weight and fuel tank volume are estimated by empirical formulae. To simplify the problem, only the leading-edge sweep angle and two chord lengths at the midspan and wingtip are used as design variables. The leading edge of the wing is kept straight. Thus, a tapered wing with a trailing-edge kink will be designed. As an optimizer, Genetic Algorithm (GA) is employed here. Because GA can find a more global optimum, it is expected to perform better than the conventional gradient-based methods. Major drawback of GA is that it requires a large number of function evaluations. Thus, FLO-22 code based on the full potential equation is used because of its efficiency instead of Euler or Navier-Stokes solver. Evaluations of GA population are parallelized an Numerical Wind Tunnel (NWT) at National Aerospace Laboratory (NAL). Planform optimization problems are considered for typical subsonic and transonic aircraft. The design results show the feasibility of the present approach for the initial sizing with optimization.","subitem_description_type":"Other"}]},"item_5_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0001433040","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-37","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":"東北大学 大学院"},{"subitem_text_value":"東北大学 工学部　機械航空工学科"},{"subitem_text_value":"東北大学 工学部　機械航空工学科"},{"subitem_text_value":"航空宇宙技術研究所"}]},"item_5_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"Tohoku University Graduate School"},{"subitem_text_language":"en","subitem_text_value":"Tohoku University Department of Aeronautics and Space Engineering, Faculty of Engineering"},{"subitem_text_language":"en","subitem_text_value":"Tohoku University Department of Aeronautics and Space Engineering, Faculty of Engineering"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"山口, 義博"}],"nameIdentifiers":[{"nameIdentifier":"479252","nameIdentifierScheme":"WEKO"}]},{"creatorNames":[{"creatorName":"大林, 茂"}],"nameIdentifiers":[{"nameIdentifier":"479253","nameIdentifierScheme":"WEKO"}]},{"creatorNames":[{"creatorName":"中橋, 和博"}],"nameIdentifiers":[{"nameIdentifier":"479254","nameIdentifierScheme":"WEKO"}]},{"creatorNames":[{"creatorName":"中村, 孝"}],"nameIdentifiers":[{"nameIdentifier":"479255","nameIdentifierScheme":"WEKO"}]},{"creatorNames":[{"creatorName":"Yamaguchi, Yoshihiro","creatorNameLang":"en"}],"nameIdentifiers":[{"nameIdentifier":"479256","nameIdentifierScheme":"WEKO"}]},{"creatorNames":[{"creatorName":"Obayashi, Shigeru","creatorNameLang":"en"}],"nameIdentifiers":[{"nameIdentifier":"479257","nameIdentifierScheme":"WEKO"}]},{"creatorNames":[{"creatorName":"Nakahashi, Kazuhiro","creatorNameLang":"en"}],"nameIdentifiers":[{"nameIdentifier":"479258","nameIdentifierScheme":"WEKO"}]},{"creatorNames":[{"creatorName":"Nakamura, Takashi","creatorNameLang":"en"}],"nameIdentifiers":[{"nameIdentifier":"479259","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":"nalsp0037040.pdf","filesize":[{"value":"770.0 kB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"nalsp0037040.pdf","url":"https://jaxa.repo.nii.ac.jp/record/37166/files/nalsp0037040.pdf"},"version_id":"9c70625b-3383-4305-b2ac-d898352a4dad"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"翼平面最適設計","subitem_subject_scheme":"Other"},{"subitem_subject":"亜音速遷音速航空機","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":"空力性能","subitem_subject_scheme":"Other"},{"subitem_subject":"翼重量","subitem_subject_scheme":"Other"},{"subitem_subject":"燃料タンク容積","subitem_subject_scheme":"Other"},{"subitem_subject":"設計変数","subitem_subject_scheme":"Other"},{"subitem_subject":"後退翼","subitem_subject_scheme":"Other"},{"subitem_subject":"NWT","subitem_subject_scheme":"Other"},{"subitem_subject":"数値風洞","subitem_subject_scheme":"Other"},{"subitem_subject":"GA","subitem_subject_scheme":"Other"},{"subitem_subject":"遺伝的アルゴリズム","subitem_subject_scheme":"Other"},{"subitem_subject":"多目的最適化","subitem_subject_scheme":"Other"},{"subitem_subject":"平面形状最適化","subitem_subject_scheme":"Other"},{"subitem_subject":"wing planform optimum design","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"subsonic transonic aircraft","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":"aerodynamic performance","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"wing weight","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"fuel tank volume","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"design variable","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"swept wing","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"NWT","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"Numerical Wind Tunnel","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"GA","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"genetic algorithm","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"multidisciplinary optimization","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"planform optimization","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":"翼平面形状の多目的最適化","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"翼平面形状の多目的最適化"}]},"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":"37166","relation_version_is_last":true,"title":["翼平面形状の多目的最適化"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T21:24:24.757492+00:00"}