{"created":"2023-06-20T15:05:11.384958+00:00","id":34454,"links":{},"metadata":{"_buckets":{"deposit":"cc0e6776-c731-4359-9bec-c2d11cc96995"},"_deposit":{"created_by":1,"id":"34454","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"34454"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00034454","sets":["1887:1890","1896:1898:1899:1992"]},"author_link":["419628"],"item_9_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1972-01","bibliographicIssueDateType":"Issued"},"bibliographicIssueNumber":"1","bibliographicPageEnd":"52","bibliographicPageStart":"1","bibliographicVolumeNumber":"37","bibliographic_titles":[{},{"bibliographic_title":"ISAS report/Institute of Space and Aeronautical Science,University of Tokyo","bibliographic_titleLang":"en"}]}]},"item_9_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"A time-dependent finite-difference method known as Fluid-in-Cell method is applied to the inviscid compressible flow problems containing such unknown discontinuities as shock wave and contact surface for the purpose of investigating the transient unsteady flow behaviour and the resulting asymptotic steady flow field as well without making any specific assumptions on the position and the strength of those discontinuities. The problems treated in the present paper are as follows : (1) supersonic flow past a circular cylinder perpendicular to the main stream, (2) supersonic flow around a flat-faced circular cylinder parallel to the main stream, and (3) supersonic flow around a flat-faced circular cylinder with a supersonic opposing jet from the nose. The results of the present numerical calculation for cases (1) and (2) show close agreement with those of the existing theories and experiments. It is also shown that, in case (1), the method of calculation can be successfully extended to the plane polar coordinate system. In case (3), it becomes clear that the present method of numerical calculation can produce sufficient informations to investigate the highly complicated flow field induced by the opposing jet. The effect of the governing parameters such as free stream and jet exit Mach numbers, nozzle to body radius ratio, and total pressure ratio of the jet to the free stream on the flow pattern are investigated. It is of interest to notice that two different types of the flow field appear according to the boundary conditions : the one is a steady flow field with a Mach disc in the jet stream and a bow shock similar to the one in front of a blunt body in the supersonic flow, and the other is an unsteady flow field with ever forward-moving bow shock and periodic wave pattern in the jet stream. The both types of flow field has already been observed in the experiments.","subitem_description_type":"Other"}]},"item_9_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: SA2400846000","subitem_description_type":"Other"}]},"item_9_publisher_8":{"attribute_name":"出版者","attribute_value_mlt":[{"subitem_publisher":"東京大学宇宙航空研究所"}]},"item_9_publisher_9":{"attribute_name":"出版者（英）","attribute_value_mlt":[{"subitem_publisher":"Institute of Space and Aeronautical Science,University of Tokyo"}]},"item_9_source_id_21":{"attribute_name":"ISSN","attribute_value_mlt":[{"subitem_source_identifier":"0372-1418","subitem_source_identifier_type":"ISSN"}]},"item_9_source_id_24":{"attribute_name":"書誌レコードID","attribute_value_mlt":[{"subitem_source_identifier":"AA00675986","subitem_source_identifier_type":"NCID"}]},"item_9_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"Research Engineer,Second Aerodynamics Division,National Aerospace Laboratory"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"HIROSE, Naoki","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":"2020-01-24"}],"displaytype":"detail","filename":"SA2400846.pdf","filesize":[{"value":"4.5 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"SA2400846.pdf","url":"https://jaxa.repo.nii.ac.jp/record/34454/files/SA2400846.pdf"},"version_id":"0e9b0288-ccb1-45f7-b546-a5ec8d4ef0a1"}]},"item_language":{"attribute_name":"言語","attribute_value_mlt":[{"subitem_language":"eng"}]},"item_resource_type":{"attribute_name":"資源タイプ","attribute_value_mlt":[{"resourcetype":"departmental bulletin paper","resourceuri":"http://purl.org/coar/resource_type/c_6501"}]},"item_title":"Numerical Calculations of Some Complicated Aerodynamic Problems by a Time-dependent Finite-difference Method","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"Numerical Calculations of Some Complicated Aerodynamic Problems by a Time-dependent Finite-difference Method","subitem_title_language":"en"}]},"item_type_id":"9","owner":"1","path":["1890","1992"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"34454","relation_version_is_last":true,"title":["Numerical Calculations of Some Complicated Aerodynamic Problems by a Time-dependent Finite-difference Method"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T23:41:46.841034+00:00"}