{"created":"2023-06-20T15:02:39.049578+00:00","id":31737,"links":{},"metadata":{"_buckets":{"deposit":"31458009-7ce6-4b4f-83f9-d7c554e4bd71"},"_deposit":{"created_by":1,"id":"31737","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"31737"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00031737","sets":["1887:1890","1896:1898:1899:1910"]},"author_link":["405981","405982","405983","405984"],"item_9_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Laminar Boundary Layer with Gas Injection on a Conical Body"}]},"item_9_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1977-08","bibliographicIssueDateType":"Issued"},"bibliographicIssueNumber":"3_A","bibliographicPageEnd":"717","bibliographicPageStart":"685","bibliographicVolumeNumber":"13","bibliographic_titles":[{"bibliographic_title":"東京大学宇宙航空研究所報告"}]}]},"item_9_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"非軸対称錐体上の吹き出しを伴う相似層流境界層に対して,微小擾乱法による1次オーダーの厳密解が提示される.以前に,本報告において,小迎角円錐上の層流境界層に対するMooreの理論を,円に近い任意断面形状をもつ錐体の場合に適用できる様に拡張した.本報告においては,境界層内への気体吹き出し(gas injection-transpiration cooling)のある場合も含め,更に理論が発展せられ,相似境界層方程式に対する厳密解が,与えられ,解の数表化が,可能となる.この場合,多孔質錐体表面から吹き出される気体の質量流束分布は,境界層が相似となる様に,錐体頂点からの距離の平方根の逆数に比例する様に与えられる.境界層外縁条件としての非粘性錐状流の解についても,Stoneの小迎角円錐に対する解析法が,一般断面形状をもつ錐体の場合へと拡張される.応用例として,M_∞=5.0における4種類の錐体を例にとり,境界層内諸特性に対する気体吹き出しの効果について議論が,なされる.その結果,気体吹き出しによる冷却効果については,交叉流面で考えると,風上側よりも,風下側における方が,より著しいことが示される.","subitem_description_type":"Abstract"}]},"item_9_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"The present paper deals with the theory of laminar boundary layer on a nonaxisymmetric conical body at supersonic flight with special reference to the effect of gas injection on the body surface. The Moore's method of solving boundary layer flow on a supersoic circular cone at small angles of attack is extended to the case of a conical body with nearly circular but otherwise arbitrary cross-section and further to the case of boundary layer with gas injection. The outer edge conditions are determined by the inviscid conical flow solution around the body obtained by an extension of the Stone's method for a circular cone. It is found that an exact similar solution to the first order perturbation equations of the boundary layer with gas injection on the conical body as stated above exists at a specific distribution of the rate of the gas injection. In case of air injection into air stream over isothermal conical body surface similarity of the boundary layer holds at the injected mass flux rate inversely proportional to the square root of the meridional distance from the body apex. The effects of mass injection on boundary layer characteristics are discussed for the cases of several shapes of conical bodies at M_∞ = 5.0 and Prandtl No. P_r = 0.738. The results show that the injection effects on heat transfer and skin friction are more significant at the leeward side than at the windward side in the cross flow plane.","subitem_description_type":"Other"}]},"item_9_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: SA0124769000","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_source_id_21":{"attribute_name":"ISSN","attribute_value_mlt":[{"subitem_source_identifier":"0563-8100","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":"AN00161914","subitem_source_identifier_type":"NCID"}]},"item_9_text_6":{"attribute_name":"著者所属","attribute_value_mlt":[{"subitem_text_value":"東京大学宇宙航空研究所"},{"subitem_text_value":"東京大学宇宙航空研究所"}]},"item_9_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"the Institute of Space and Aeronautical Science University of Tokyo"},{"subitem_text_language":"en","subitem_text_value":"the Institute of Space and Aeronautical Science University of Tokyo"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"松野, 謙一"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"河村, 龍馬"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"MATSUNO, Ken-ichi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"KAWAMURA, Ryuma","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":"2020-01-23"}],"displaytype":"detail","filename":"SA0124769.pdf","filesize":[{"value":"1.2 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"SA0124769.pdf","url":"https://jaxa.repo.nii.ac.jp/record/31737/files/SA0124769.pdf"},"version_id":"9df1786b-ceac-4512-a990-53065ccd181e"}]},"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":"departmental bulletin paper","resourceuri":"http://purl.org/coar/resource_type/c_6501"}]},"item_title":"錐体上の気体吹き出しを伴う層流境界層","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"錐体上の気体吹き出しを伴う層流境界層"}]},"item_type_id":"9","owner":"1","path":["1890","1910"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"31737","relation_version_is_last":true,"title":["錐体上の気体吹き出しを伴う層流境界層"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-21T00:52:05.875296+00:00"}