{"created":"2023-06-20T15:10:19.125359+00:00","id":39902,"links":{},"metadata":{"_buckets":{"deposit":"ba2ebc07-7adf-4ddc-8133-d62f1a30dc6c"},"_deposit":{"created_by":1,"id":"39902","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"39902"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00039902","sets":["1887:1893","1896:1898:1913:1917"]},"author_link":["445574","445573","445572","445575"],"item_3_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Employment of kappa-epsilon turbulence model for finite-element analysis of flows over single- and multi-component aerofoils"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1996-12","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"19","bibliographicPageStart":"1","bibliographicVolumeNumber":"1316","bibliographic_titles":[{"bibliographic_title":"航空宇宙技術研究所報告"},{"bibliographic_title":"Technical Report of National Aerospace Laboratory","bibliographic_titleLang":"en"}]}]},"item_3_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"非圧縮性ナビエ・ストークスの式を有限要素法によって解く計算コードに、高レイノルズ数型のκ-ε乱流モデルを組み合わせて、翼型まわりの流れを数値的に解くことを試みた。解くべき方程式は非線形性が強く、発散しやすい性質を持つが、陰的オイラースキームを用いて時間積分を実行し、さらに一様流中に潜在する乱れの存在を仮定した結果、安定な流れの解を得ることができた。迎角、フラップの偏角があまり大きくない場合の比較的おとなしい流れに対しては、計算で得られた翼型まわりの圧力分布、揚力は実験結果と良く一致し、この乱流モデルを用いる有効性が確認できた。しかし、流れが時間とともに振動する場合や、迎角の大きい場合には、実験値と計算値の一致の度合いは低くなった。陰的オイラースキームの採用に伴って必要となった大規模な1次方程式系の解法として、できる限り少ない計算メモリで高速に解の得られる直接解法コードを新たに開発して用いた。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"Finite-element analysis code to solve incompressible Navier-Stokes equations was incorporated into the kappa-epsilon turbulence model of high Reynolds number type, and was applied to flows around single- and multicomponent aerofoils. Although the relevant equations are highly nonlinear and, therefore, their solutions are easy to diverge, the employment of the implicit Euler scheme for time marching integral and the introduction of background turbulence in the uniform flow made it possible to obtain stable solutions. For gentle flows produced around aerofoils at moderate angles of attack or aerofoils with a flap and slat at moderate deflection angles, the computed pressure distributions around the aerofoils and lift coefficients as well are in good agreement with measured results. The effectiveness of the turbulence model for such complicated flows was assured from this fact. For the flows which oscillated periodically or corresponded to aerofoils at high angles of attack, however, there was less agreement between computed and measured results. To solve a large-scale linear equation system, which was necessitated by the adoption of the implicit Euler scheme, a newly developed code for the direct method was used successfully.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0000880000","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 TR-1316","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":"0389-4010","subitem_source_identifier_type":"ISSN"}]},"item_3_text_6":{"attribute_name":"著者所属","attribute_value_mlt":[{"subitem_text_value":"航空宇宙技術研究所 新型航空機研究グループ"},{"subitem_text_value":"航空宇宙技術研究所 新型航空機研究グループ"}]},"item_3_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Advanced Aircraft Research Group"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Advanced Aircraft Research Group"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"重見, 仁"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"伊藤, 婦美子"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Shigemi, Masashi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Ito, Fumiko","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":"2020-01-27"}],"displaytype":"detail","filename":"naltr01316.pdf","filesize":[{"value":"2.3 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"naltr01316.pdf","url":"https://jaxa.repo.nii.ac.jp/record/39902/files/naltr01316.pdf"},"version_id":"0ecf8969-3f02-4f90-ac00-d7c5570caa7e"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"乱流モデル","subitem_subject_scheme":"Other"},{"subitem_subject":"カッパ・エプシロン乱流モデル","subitem_subject_scheme":"Other"},{"subitem_subject":"単翼素","subitem_subject_scheme":"Other"},{"subitem_subject":"多翼素","subitem_subject_scheme":"Other"},{"subitem_subject":"非圧縮流れ","subitem_subject_scheme":"Other"},{"subitem_subject":"有限要素法","subitem_subject_scheme":"Other"},{"subitem_subject":"ナビエ・ストークス方程式","subitem_subject_scheme":"Other"},{"subitem_subject":"レイノルズ数","subitem_subject_scheme":"Other"},{"subitem_subject":"オイラースキーム","subitem_subject_scheme":"Other"},{"subitem_subject":"陰的オイラースキーム","subitem_subject_scheme":"Other"},{"subitem_subject":"迎角","subitem_subject_scheme":"Other"},{"subitem_subject":"フラップ偏角","subitem_subject_scheme":"Other"},{"subitem_subject":"翼まわり圧力分布","subitem_subject_scheme":"Other"},{"subitem_subject":"揚力係数","subitem_subject_scheme":"Other"},{"subitem_subject":"turbulence model","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"kappa epsilon turbulence model","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"single component aerofoil","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"multicomponent aerofoil","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"incompressible flow","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"finite element method","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"Navier Stokes equation","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"Reynolds number","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"Euler scheme","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"implicit Euler scheme","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"attack angle","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"flap angle","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"pressure distribution around aerofoil","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"lift coefficient","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":"technical report","resourceuri":"http://purl.org/coar/resource_type/c_18gh"}]},"item_title":"κ-ε乱流モデルを用いた単翼素および多翼素型まわり非圧縮流れの有限要素法による解析","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"κ-ε乱流モデルを用いた単翼素および多翼素型まわり非圧縮流れの有限要素法による解析"}]},"item_type_id":"3","owner":"1","path":["1893","1917"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"39902","relation_version_is_last":true,"title":["κ-ε乱流モデルを用いた単翼素および多翼素型まわり非圧縮流れの有限要素法による解析"],"weko_creator_id":"1","weko_shared_id":1},"updated":"2023-06-20T19:18:20.465980+00:00"}