{"created":"2023-06-20T15:08:21.837028+00:00","id":37792,"links":{},"metadata":{"_buckets":{"deposit":"c0a851fe-3e87-44bd-80d5-4f25edd75196"},"_deposit":{"created_by":1,"id":"37792","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"37792"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00037792","sets":["1887:1891","1896:1898:1913:1915"]},"author_link":["483011","483013","483012","483014"],"item_5_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"The three-dimensional numerical analysis of injection into a supersonic flow"}]},"item_5_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1994-03","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"190","bibliographicPageStart":"185","bibliographicVolumeNumber":"22","bibliographic_titles":[{"bibliographic_title":"航空宇宙技術研究所特別資料: 第11回航空機計算空気力学シンポジウム論文集"},{"bibliographic_title":"Special Publication of National Aerospace Laboratory: Proceedings of the 11th NAL Symposium on aircraft computational aerodynamics","bibliographic_titleLang":"en"}]}]},"item_5_description_14":{"attribute_name":"会議概要（会議名, 開催地, 会期, 主催者等）","attribute_value_mlt":[{"subitem_description":"航空宇宙技術研究所 10-11 Jun. 1993 東京 日本","subitem_description_type":"Other"}]},"item_5_description_15":{"attribute_name":"会議概要（会議名, 開催地, 会期, 主催者等）（英）","attribute_value_mlt":[{"subitem_description":"National Aerospace Laboratory 10-11 Jun. 1993 Tokyo Japan","subitem_description_type":"Other"}]},"item_5_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"3次元ナビエ・ストークス方程式と2化学種保存方程式を解くことにより有限長さのスリットから直角に空気噴射を行う場合の超音速流れと混合の場を調べた。乱流モデルとして、ラージエディシミュレーションのサブグリッドスケールモデルを用いた。支配方程式の対流項にYeeタイプのTVD風上スキームを適用し、散逸項については中心差分を用いた。時間積分はLU分解陰解法を用いた。スリットの向きが90度と45度の2つの場合を扱った。3次元数値計算法の信頼性を確かめるため実験による測定を行った。ピトー圧力分布について数値計算結果を実測値と比較し、定性的および定量的にかなりよく一致する結果を得た。数値シミュレーションでは、混合場を調べるために主流と噴射された空気とは異なる化学種として取り扱った。90度スリットの場合、スリットが十分長いにも拘わらず、流れと混合場は端の存在のため3次元的となる。45度スリットの場合は3次元性がさらに強くなり、混合が促進される。いずれの場合も、スリットの下流側に到達する主流の部分はスリット端近傍の渦流よりも高い程度で混合の増進に影響する。","subitem_description_type":"Abstract"}]},"item_5_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"The supersonic flow and mixing fields with a perpendicular air injection from a finite length slit are investigated by solving the three dimensional full Navier-Stokes equations and the two chemical species conservative equations. As the turbulent model, the subgrid scale model of the large eddy simulation is employed. The Yee's type upwind total variation diminishing scheme is applied for the convective terms of the governing equations. The dissipation terms are evaluated by the central difference. The time integration is performed by using the Lower-Upper factored implicit method. Two slit angle cases of 90 deg and 45 deg are treated. The experimental measurements are performed in order to confirm the reliability of the three dimensional numerical code. The numerical results are compared with the experimental ones as regards the Pitot pressure distributions. The numerical results fairly agree with the experimental data both qualitatively and quantitatively. In the numerical simulation, the main flow air and the injected air arc treated as the different species, so the mixing fields can be examined. From the results in case of the 90 deg slit angle, even though the injection slit is long enough, the flow and mixing fields are rather three dimensional because of the existence of both side ends. All the results show that a part of the main flow which gets into downstream side of the slit influences on the mixing augmentation in the higher order than the vortex flow in the vicinity of the slit ends.","subitem_description_type":"Other"}]},"item_5_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0004171032","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: NAL SP-22","subitem_description_type":"Other"}]},"item_5_publisher_8":{"attribute_name":"出版者","attribute_value_mlt":[{"subitem_publisher":"航空宇宙技術研究所"}]},"item_5_publisher_9":{"attribute_name":"出版者（英）","attribute_value_mlt":[{"subitem_publisher":"National Aerospace Laboratory (NAL)"}]},"item_5_source_id_21":{"attribute_name":"ISSN","attribute_value_mlt":[{"subitem_source_identifier":"0289-260X","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":"AN10097345","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":"東京大学 工学部　航空宇宙工学科"}]},"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":"University of Tokyo Department of Aeronautics and Astronautics, Faculty of Engineering"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"横田, 和彦"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"梶, 昭次郎"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Yokota, Kazuhiko","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Kaji, Shojiro","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":"2020-02-10"}],"displaytype":"detail","filename":"nalsp0022031.pdf","filesize":[{"value":"544.3 kB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"nalsp0022031.pdf","url":"https://jaxa.repo.nii.ac.jp/record/37792/files/nalsp0022031.pdf"},"version_id":"d355bf4e-5c1c-4d90-a5f5-5f8cd04d93a9"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"超音速流噴射","subitem_subject_scheme":"Other"},{"subitem_subject":"燃料噴射","subitem_subject_scheme":"Other"},{"subitem_subject":"スクラムジェットエンジン","subitem_subject_scheme":"Other"},{"subitem_subject":"超音速燃焼","subitem_subject_scheme":"Other"},{"subitem_subject":"燃料空気混合メカニズム","subitem_subject_scheme":"Other"},{"subitem_subject":"燃料空気混合判定基準","subitem_subject_scheme":"Other"},{"subitem_subject":"化学反応流れ","subitem_subject_scheme":"Other"},{"subitem_subject":"空気水素混合流れ","subitem_subject_scheme":"Other"},{"subitem_subject":"混合効率","subitem_subject_scheme":"Other"},{"subitem_subject":"混合流れ全圧損失","subitem_subject_scheme":"Other"},{"subitem_subject":"流れ数値シミュレーション","subitem_subject_scheme":"Other"},{"subitem_subject":"CFD解析","subitem_subject_scheme":"Other"},{"subitem_subject":"ナビエ・ストークス方程式数値解","subitem_subject_scheme":"Other"},{"subitem_subject":"サブグリッドスケールモデル応用","subitem_subject_scheme":"Other"},{"subitem_subject":"計算空気力学","subitem_subject_scheme":"Other"},{"subitem_subject":"supersonic flow injection","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"fuel injection","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"scramjet engine","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"supersonic combustion","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"fuel air mixing mechanism","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"fuel air mixing criterion","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"chemically reacting flow","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"air hydrogen mixed flow","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"mixing efficiency","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"mixing flow total pressure loss","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"numerical flow simulation","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"CFD analysis","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"Navier Stokes equation numerical solution","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"subgrid scale model utilization","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"Computational Fluid Dynamics","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":"超音速流中への噴射に関する3次元数値解析","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"超音速流中への噴射に関する3次元数値解析"}]},"item_type_id":"5","owner":"1","path":["1891","1915"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"37792","relation_version_is_last":true,"title":["超音速流中への噴射に関する3次元数値解析"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T21:12:15.808047+00:00"}