{"created":"2023-06-20T15:15:06.400420+00:00","id":45160,"links":{},"metadata":{"_buckets":{"deposit":"48f61cf3-0613-4dd0-b2b7-2e18c2bae2c2"},"_deposit":{"created_by":1,"id":"45160","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"45160"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00045160","sets":["1887:1893","1896:1898:1913:1917"]},"author_link":["473203","473200","473199","473198","473202","473201"],"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1986-03","bibliographicIssueDateType":"Issued"},"bibliographicPageStart":"16","bibliographicVolumeNumber":"901T","bibliographic_titles":[{},{"bibliographic_title":"Technical Report of National Aerospace Laboratory TR-901T","bibliographic_titleLang":"en"}]}]},"item_3_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"任意に指定した圧力分布を実現する,ナビエ・ストークス方程式に基づく遷音速翼型設計の反復的手順を提案する。本手順は,基本圧力分布と指定圧力分布との間の差に対する翼型形状修正項に関する逆問題の遷音速積分方程式による設計法と,翼型に対する高レイノルズ数遷音速流の時間平均ナビエ・ストークス解析コード,NSFOIL,との結合によって組立てられる。NSFOILはBeam-Warming-Stegerの陰的近似因子化(IAF)法に,陰的な翼,伴流境界条件化等の改良を加えた差分法を用いた解析法である。解析法は,衝撃波や弱い剥離を含む粘性効果を適切に評価することが可能であり,従って,設計手順に,これらの効果を正しく評価することができる。衝撃波無し圧力分布と超臨界圧力分布に対する数値解析例を示す。数回の反復によって,実用的に満足な翼型形状を得ることができた。本手順は低速翼型設計にも,より容易に適用することが出来る。その例として,通常な圧力分布と,新しい型の圧力分布に対する設計例をも,あわせて示す。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"An iterative procedure for transonic airfoil design based on the Navier-Stokes equations to attain arbitrarily specified pressure distributions is proposed in this paper. A transonic integral equation for the inverse problem for the correction term between the basic pressure distribution and the specified pressure distribution is fomulated and is combined with a time-averaged Navier-Stokes airfoil analysis code. Shock wave and viscous effects including weak separation are properly evaluated in the analysis mode and therefore are effectively incorporated in the design procedure. Numerical results for a shockless pressure distribution and a supercritical pressure distribution are presented. A small number of iterative steps yield almost satisfactory airfoil geometry in practical point of view. The method is also applied to low speed airfoil designs and the results are shown.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: NALTR0901000","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 TR-901T","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":"0389-4010","subitem_source_identifier_type":"ISSN"}]},"item_3_text_6":{"attribute_name":"著者所属","attribute_value_mlt":[{"subitem_text_value":"航空宇宙技術研究所空気力学第二部"},{"subitem_text_value":"航空宇宙技術研究所空気力学第二部"},{"subitem_text_value":"航空宇宙技術研究所空気力学第二部"}]},"item_3_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"Second Aerodynamics Division, National Aerospace Laboratory(NAL)"},{"subitem_text_language":"en","subitem_text_value":"Second Aerodynamics Division, National Aerospace Laboratory(NAL)"},{"subitem_text_language":"en","subitem_text_value":"Second Aerodynamics Division, National Aerospace Laboratory(NAL)"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"廣瀬, 直喜"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"高梨, 進"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"河合, 伸坦"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"HIROSE, Naoki","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"TAKANASHI, Susumu","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"KAWAI, Nobuhiro","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":"2020-01-29"}],"displaytype":"detail","filename":"naltr0901t.pdf","filesize":[{"value":"1.2 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"naltr0901t.pdf","url":"https://jaxa.repo.nii.ac.jp/record/45160/files/naltr0901t.pdf"},"version_id":"89583b40-1851-4a12-b0dc-49a03ce4a121"}]},"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":"technical report","resourceuri":"http://purl.org/coar/resource_type/c_18gh"}]},"item_title":"Transonic Airfoil Design Based on the Navier-Stokes Equations to Attian Arbitrarily Specified Pressure Distribution -An Iterative Procedure-","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"Transonic Airfoil Design Based on the Navier-Stokes Equations to Attian Arbitrarily Specified Pressure Distribution -An Iterative Procedure-","subitem_title_language":"en"}]},"item_type_id":"3","owner":"1","path":["1893","1917"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"45160","relation_version_is_last":true,"title":["Transonic Airfoil Design Based on the Navier-Stokes Equations to Attian Arbitrarily Specified Pressure Distribution -An Iterative Procedure-"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T21:44:16.092526+00:00"}