{"created":"2023-06-20T15:07:30.777177+00:00","id":36879,"links":{},"metadata":{"_buckets":{"deposit":"62be9ef1-d2e6-4eb3-a08c-6515eb1e777b"},"_deposit":{"created_by":1,"id":"36879","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"36879"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00036879","sets":["1887:1891","1896:1898:1913:1915"]},"author_link":["477981","477986","477983","477982","477980","477985","477979","477984"],"item_5_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Three-dimensional aerodynamic optimization"}]},"item_5_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1997-01","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"112","bibliographicPageStart":"107","bibliographicVolumeNumber":"34","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 6-7 JUN. 1996 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 6-7 JUN. 1996 Tokyo Japan","subitem_description_type":"Other"}]},"item_5_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"ナビエ・ストークス数値計算を用いた一般亜音速輸送機用の空力翼形状の最適化に遺伝的アルゴリズム(GA)を適用した。通常の最適化スキームは局所的な最適解にとどまるので空力最適化問題には適していない。GAは多方向的に探索するので、結果的に空力最適化アルゴリズムは大域的な最適解を見つけ出す。さらに、アルゴリズム自体が極めて単純で、非常にロバストである。しかし、GAは膨大な計算時間を必要とする。前回の研究で、GAとナビエ・ストークス計算による翼形状の2次元最適化計算にはCRAY-C90の単一プロセッサ当たり数百CPU時間を必要とすることを指摘した。この研究で、GAによる3次元最適化にはスーパーコンピュータでも受け入れがたいほどのCPU時間を必要とすることに気付いた。したがって、翼のL/D(揚抗比)を正確に評価するのにナビエ・ストークス計算を必要とするにもかかわらず、これまでGAおよびナビエ・ストークス計算による翼形状の3次元最適化を行わなかった。この最適化に必要な膨大なCPU時間を克服するために、(1)スパン方向の最大翼厚分布とねじり角分布を設計変数として選定し、(2)多重格子法を3次元ナビエ・ストークス計算に適用し、(3)166の処理素子を有する並列ベクトル機である航空宇宙技術研究所の数値風洞を用いて計算を並列化した。本研究の最適化目的は翼形状のL/Dを最大にすることである。高速度中の低い抗力に対し翼厚さゼロという見掛け上の解が出るのを避けるために、構造上の制限を考案した。本研究のGAから得た最適設計の中で、既存の理論と経験から開発した翼に対する設計原理が具体化されることが分かった。このことは高次コンピュータ環境にあって、空力最適化に対する現在の研究法が実現可能であることを示している。","subitem_description_type":"Abstract"}]},"item_5_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"A Genetic Algorithm (GA) has been applied to optimize a wing aerodynamic shape for generic subsonic transport aircraft using Navier-Stokes computations. Conventional optimization schemes are not suitable for aerodynamic optimization problems as they fall into a local optimum. Since a GA searches multi-directionally, the resulting aerodynamic optimization algorithm finds a global optimum. Moreover, as the algorithm itself is very simple and thus very robust. However, a GA needs enormous computational time. Previous study indicated that 2-D optimization of airfoil shape with GA and Navier-Stokes calculation needs several hundred CPU time on CRAY C90 single processor. From this study, it was realized that 3-D optimization with GA will require unacceptable CPU time even on a supercomputer. Thus, any 3-D optimization of wing shape has never been done before with a GA and Navier-Stokes calculation though Navier-Stokes calculation is necessary to evaluate L/D (Lift to Drag ratio) of a wing precisely. In this study, to overcome enormous CPU time necessary for this optimization: (1) spanwise maximum thickness and twist angle distributions are selected as design variables; (2) the multigrid technique is applied to the 3-D Navier-Stokes computation; and (3) the computation is parallelized on numerical wind tunnel at National Aerospace Laboratory, which is a parallel vector machine with 166 processing elements. The objective of the present optimization is to maximize L/D of wing shape. To avoid apparent solution of zero thickness wing for low drag in high speed, a structural constraint is considered. In the optimum design obtained from the present GA, the design principles for the wing developed by existing theory and experience are found to be materialized. This indicates feasibility of the present approach for the aerodynamic optimization in advanced computational environments.","subitem_description_type":"Other"}]},"item_5_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0000685020","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-34","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 大学院"},{"subitem_text_value":"東北大学 大学院"},{"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 Graduate School"},{"subitem_text_language":"en","subitem_text_value":"Tohoku University Graduate School"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"大山, 聖"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"大林, 茂"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"中橋, 和博"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"中村, 孝"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Oyama, Akira","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Obayashi, Shigeru","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Nakahashi, Kazuhiro","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Nakamura, Takashi","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":"nalsp0034020.pdf","filesize":[{"value":"668.7 kB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"nalsp0034020.pdf","url":"https://jaxa.repo.nii.ac.jp/record/36879/files/nalsp0034020.pdf"},"version_id":"21be29e0-2384-4f6b-84ef-ec6ffd20394f"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"空力最適化","subitem_subject_scheme":"Other"},{"subitem_subject":"3次元翼","subitem_subject_scheme":"Other"},{"subitem_subject":"多重格子法","subitem_subject_scheme":"Other"},{"subitem_subject":"遺伝的アルゴリズム","subitem_subject_scheme":"Other"},{"subitem_subject":"ナビエ・ストークス方程式","subitem_subject_scheme":"Other"},{"subitem_subject":"空力翼形状","subitem_subject_scheme":"Other"},{"subitem_subject":"亜音速輸送機","subitem_subject_scheme":"Other"},{"subitem_subject":"FAS","subitem_subject_scheme":"Other"},{"subitem_subject":"full approximation scheme","subitem_subject_scheme":"Other"},{"subitem_subject":"ねじり角分布","subitem_subject_scheme":"Other"},{"subitem_subject":"NWT","subitem_subject_scheme":"Other"},{"subitem_subject":"数値風洞","subitem_subject_scheme":"Other"},{"subitem_subject":"aerodynamic optimization","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"three dimensional wing","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"multigrid technique","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"genetic algorithm","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"Navier Stokes equation","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"wing aerodynamic shape","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"subsonic transport aircraft","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"FAS","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"full approximation scheme","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"twist angle distribution","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"}]},"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":"三次元翼の空力最適化","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"三次元翼の空力最適化"}]},"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":"36879","relation_version_is_last":true,"title":["三次元翼の空力最適化"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T21:29:57.683848+00:00"}