{"created":"2023-06-20T15:13:12.341710+00:00","id":43125,"links":{},"metadata":{"_buckets":{"deposit":"d906ef65-c3ff-4216-812a-eb301c9da947"},"_deposit":{"created_by":1,"id":"43125","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"43125"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00043125","sets":["1887:1893","1896:1898:1913:1915"]},"author_link":["462326","462327"],"item_3_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Numerical Analyses in Aerodynamic Design of Aero-Engine Fan"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1983-11","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"62","bibliographicPageStart":"55","bibliographicVolumeNumber":"1","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 SP-1","bibliographic_titleLang":"en"}]}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"A brief review is presented of the current status of numerical methods for aero-engine fan internal flow analyses used in the design stage. 1) Meridional flow analysis For this axisymmetric, mostly subsonic flow regime, the streamline curvature method has been most widely used, followed by the matrix method FEM, with recent remarkable advancement, is also becoming a useful tool. 2) Transonic cascade flow analysis For the fan rotor outer region where the total pressure losses associated with shock waves play an important role, 2-D shock-capturing Euler codes are relevant, and schemes such as MacCormack's or Denton's are commonly built into standard design procedures. The Navier-Stokes codes need some time before becoming a standard technique for this purpose. 3) Supercritical cascade design analysis Supercritical airfoil technology developed for airclaft wings finds application in the cascade design. Both inverse method, such as the Bauer-Garabedian-Korn method using complex potentials, and direct methods with transonic potential analysis are utilized in this application. 4) 3-D blade-to-blade analysis 3-D Euler codes are used to check the 3-D effects within blade-to-blade passage. Computational speed is the major requirement, and presently the first-order FVM is mot popular. 5) Circumferential pressure distribution analysis The singularity distribution method with compressibility correction has proved useful for assessing the circumferential pressure distribution induced by downstream obstacles such as struts, which significantly affect the performance of rotors and stators of a fan.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: NALSP0001007","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 SP-1","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":"0289-260X","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":"AN10097345","subitem_source_identifier_type":"NCID"}]},"item_3_text_6":{"attribute_name":"著者所属","attribute_value_mlt":[{"subitem_text_value":"石川島播磨重工業株式会社"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"永野, 進"}],"nameIdentifiers":[{"nameIdentifier":"462326","nameIdentifierScheme":"WEKO"}]},{"creatorNames":[{"creatorName":"Nagano, Susumu","creatorNameLang":"en"}],"nameIdentifiers":[{"nameIdentifier":"462327","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":"2020-01-28"}],"displaytype":"detail","filename":"nalsp0001007.pdf","filesize":[{"value":"507.4 kB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"nalsp0001007.pdf","url":"https://jaxa.repo.nii.ac.jp/record/43125/files/nalsp0001007.pdf"},"version_id":"0b07698d-72e5-421f-852f-46fb3941d818"}]},"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":"航空エンジン用ファン空力設計における数値解析","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"航空エンジン用ファン空力設計における数値解析"}]},"item_type_id":"3","owner":"1","path":["1893","1915"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"43125","relation_version_is_last":true,"title":["航空エンジン用ファン空力設計における数値解析"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T22:22:19.805955+00:00"}