{"created":"2023-06-20T14:35:47.504848+00:00","id":2070,"links":{},"metadata":{"_buckets":{"deposit":"a65200e7-2f0b-4390-b172-58a05eab1f54"},"_deposit":{"created_by":1,"id":"2070","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"2070"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00002070","sets":["1887:1893","9:10:106:1941"]},"author_link":["2836","2837","2840","2839","2838","2835"],"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"2010-05-31","bibliographicIssueDateType":"Issued"},"bibliographicVolumeNumber":"JAXA-RR-10-001E","bibliographic_titles":[{"bibliographic_title":"宇宙航空研究開発機構研究開発報告"},{"bibliographic_title":"JAXA Research and Development Report","bibliographic_titleLang":"en"}]}]},"item_3_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"新規に開発された回転翼流れ場ソルバー rFlow3D が一様流に配置された単独胴体，およびロータ・胴体の組み合わせに対して適用され，周囲の流れ場及びロータ・胴体間の干渉現象が解析された. 導入された SLAU スキームは Simple Low-dissipative AUSM (Advection Upstream Splitting Method) の略であり，局所前処理数値スキームの一種である. ヘリコプタのロータ・ブレードのような移動変形する物体周りの流れ場にも対応できるように，原型の SLAU スキームに対して，若干修正を加えた. このスキームの導入によりマッハ0. 01 以下という極低速域と遷音速域での正確な抗力係数値を同時に計算することが可能になった. この良好な特性はヘリコプタ周辺の複雑な流れ場の予測に適していると考えられている. ソルバーは重合格子を利用し，単独胴体及びロータ・胴体の組み合わせの両シミュレーションにおいて ROBIN 型胴体が適用された. 制御変数や条件の設定値については実験の値がそのまま使われ，流れ場の計算出力値は実験のそれと比較された. 新しく開発されたソルバーにより十分な結果が得られた. ロータ・ブレード付け根，その他の低速域での流れ場の解析精度は改善され，現時点におけるテスト計算の結果は満足できるものであり，ヘリコプタ周辺の流れ場解析への将来の適用にも期待できるものである.","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"A newly developed rotor flow solver: rFlow3D is applied to an isolated helicopter fuselage in the freestream, and then to a rotor/fuselage combination to analyze the surrounding flow field and study the effects due to the rotor/fuselage interaction. The modified SLAU scheme, which stands for Simple Low-dissipative AUSM (Advection Upstream Splitting Method), is a type of locally preconditioned numerical scheme. It enables the solver to calculate realistic drag coeffi cient values even at low speeds under Mach 0.01 as well as those at transonic speeds. This favorable feature of the scheme is suitable for the challenging demands for predicting the flow fields surrounding helicopters. The solver is based on overlapped grid approach. The ROBIN type fuselage was adopted as the geometry for both the isolated fuselage and rotor/fuselage simulations. Experimental settings for the controls and other conditions are used in the calculations. The resulting flow field variables were then compared to the experimental measurements. It was concluded that the newly developed code provides satisfactory results. Flow features around the rotor blade root and in other low speed areas are improved and test calculations to date are promising for future applications in the analysis of flow fields surrounding helicopters.","subitem_description_type":"Other"}]},"item_3_description_18":{"attribute_name":"内容記述","attribute_value_mlt":[{"subitem_description":"形態: カラー図版あり","subitem_description_type":"Other"}]},"item_3_description_19":{"attribute_name":"内容記述（英）","attribute_value_mlt":[{"subitem_description":"Physical characteristics: Original contains color illustrations","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0064643000","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: JAXA-RR-10-001E","subitem_description_type":"Other"}]},"item_3_publisher_8":{"attribute_name":"出版者","attribute_value_mlt":[{"subitem_publisher":"宇宙航空研究開発機構"}]},"item_3_publisher_9":{"attribute_name":"出版者（英）","attribute_value_mlt":[{"subitem_publisher":"Japan Aerospace Exploration Agency (JAXA)"}]},"item_3_source_id_21":{"attribute_name":"ISSN","attribute_value_mlt":[{"subitem_source_identifier":"1349-1113","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":"AA1192675X","subitem_source_identifier_type":"NCID"}]},"item_3_text_6":{"attribute_name":"著者所属","attribute_value_mlt":[{"subitem_text_value":"宇宙航空研究開発機構（調布）"},{"subitem_text_value":"宇宙航空研究開発機構（調布）"},{"subitem_text_value":"東京ビジネスサービス"}]},"item_3_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"Japan Aerospace Exploration Agency (JAXA)"},{"subitem_text_language":"en","subitem_text_value":"Japan Aerospace Exploration Agency (JAXA)"},{"subitem_text_language":"en","subitem_text_value":"Tokyo Business Service"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"田辺, 安忠"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"齊藤, 茂"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"大谷, 一平"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Tanabe, Yasutada","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Saito, Shigeru","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Otani, Ippei","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":"2020-01-15"}],"displaytype":"detail","filename":"64643000.pdf","filesize":[{"value":"3.4 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"64643000.pdf","url":"https://jaxa.repo.nii.ac.jp/record/2070/files/64643000.pdf"},"version_id":"ca00578f-2852-45d3-ab14-e811ee3f7896"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"Helicopter, CFD, SLAU scheme, Overlapped grids, rFlow3D","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":"Validation of Computational Results of Rotor/Fuselage Interaction Analysis Using rFlow3D Code","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"Validation of Computational Results of Rotor/Fuselage Interaction Analysis Using rFlow3D Code","subitem_title_language":"en"}]},"item_type_id":"3","owner":"1","path":["1893","1941"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"2070","relation_version_is_last":true,"title":["Validation of Computational Results of Rotor/Fuselage Interaction Analysis Using rFlow3D Code"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-21T09:29:10.893166+00:00"}