{"created":"2023-06-20T14:39:14.638758+00:00","id":5954,"links":{},"metadata":{"_buckets":{"deposit":"9dd657ca-0fb7-4d4c-aa27-486e76ff8734"},"_deposit":{"created_by":1,"id":"5954","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"5954"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00005954","sets":["1887:1891","9:789:998:1024"]},"author_link":["29476","29478","29477","29475"],"item_5_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Characteristics of flow field around the delta wing at various angles of attack and Mach numbers chordwise transitions of flow field"}]},"item_5_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"2006-12-01","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"55","bibliographicPageStart":"50","bibliographicVolumeNumber":"JAXA-SP-06-010","bibliographic_titles":[{"bibliographic_title":"宇宙航空研究開発機構特別資料: 航空宇宙数値シミュレーション技術シンポジウム2006論文集"},{"bibliographic_title":"JAXA Special Publication: Proceedings of Aerospace Numerical Simulation Symposium 2006","bibliographic_titleLang":"en"}]}]},"item_5_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"Flows over a 65-degrees sweep delta wing with a sharp leading edge at various angles of attack and various Mach numbers are computationally studied. Computational simulations show that there are some conditions where the flow fields transit in chordwise direction. There appear three kinds of chordwise transitions of flow fields; (1) vortex breakdown above the delta wing at high angles of attack and subsonic flow conditions, (2) shock wave normal to the chordwise direction at center of the delta wing at high angles of attack and transonic flow conditions, which often accompanies vortex breakdown, and (3) intermediate flow fields that include two different types of flow in chordwise direction in the border area between two different flow types. Computational simulations also show that there is close correlation between breakdown and normal shock wave at the center of the wing at high angles of attack and transonic flow conditions. The results also show that vortex structure and two types of shock wave are related closely each other in the intermediate flow fields in chordwise direction.","subitem_description_type":"Other"}]},"item_5_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0063154010","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: JAXA-SP-06-010","subitem_description_type":"Other"}]},"item_5_publisher_8":{"attribute_name":"出版者","attribute_value_mlt":[{"subitem_publisher":"宇宙航空研究開発機構"}]},"item_5_publisher_9":{"attribute_name":"出版者（英）","attribute_value_mlt":[{"subitem_publisher":"Japan Aerospace Exploration Agency (JAXA)"}]},"item_5_source_id_21":{"attribute_name":"ISSN","attribute_value_mlt":[{"subitem_source_identifier":"1349-113X","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":"AA11984031","subitem_source_identifier_type":"NCID"}]},"item_5_text_6":{"attribute_name":"著者所属","attribute_value_mlt":[{"subitem_text_value":"東京大学 大学院"},{"subitem_text_value":"宇宙航空研究開発機構"}]},"item_5_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"University of Tokyo Graduate School"},{"subitem_text_language":"en","subitem_text_value":"Japan Aerospace Exploration Agency"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"今井, 源太"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"藤井, 孝藏"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Imai, Genta","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Fujii, Kozo","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":"2020-01-16"}],"displaytype":"detail","filename":"63154010.pdf","filesize":[{"value":"1.9 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"63154010.pdf","url":"https://jaxa.repo.nii.ac.jp/record/5954/files/63154010.pdf"},"version_id":"0b774adc-c246-4f52-a894-26c3456c08b2"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"流れの分布","subitem_subject_scheme":"Other"},{"subitem_subject":"デルタ翼","subitem_subject_scheme":"Other"},{"subitem_subject":"迎角","subitem_subject_scheme":"Other"},{"subitem_subject":"マッハ数","subitem_subject_scheme":"Other"},{"subitem_subject":"渦崩壊","subitem_subject_scheme":"Other"},{"subitem_subject":"ナビエ・ストークス方程式","subitem_subject_scheme":"Other"},{"subitem_subject":"数値解析","subitem_subject_scheme":"Other"},{"subitem_subject":"渦","subitem_subject_scheme":"Other"},{"subitem_subject":"渦構造","subitem_subject_scheme":"Other"},{"subitem_subject":"剥離渦","subitem_subject_scheme":"Other"},{"subitem_subject":"AUSMDV","subitem_subject_scheme":"Other"},{"subitem_subject":"MUSCL","subitem_subject_scheme":"Other"},{"subitem_subject":"flow distribution","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"delta wing","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"angle of attack","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"Mach number","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"vortex breakdown","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"Navier-Stokes equation","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"numerical analysis","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"vortex","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"vortex structure","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"separated vortex","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"AUSMDV","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"MUSCL","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":"様々な迎角・マッハ数におけるデルタ翼周りの流れ場特性コード方向の流れ場変化","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"様々な迎角・マッハ数におけるデルタ翼周りの流れ場特性コード方向の流れ場変化"}]},"item_type_id":"5","owner":"1","path":["1024","1891"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"5954","relation_version_is_last":true,"title":["様々な迎角・マッハ数におけるデルタ翼周りの流れ場特性コード方向の流れ場変化"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-21T08:05:20.018644+00:00"}