{"created":"2023-06-20T15:15:15.895877+00:00","id":45334,"links":{},"metadata":{"_buckets":{"deposit":"bc9cae85-c5ea-4125-957e-863ee44ddc0c"},"_deposit":{"created_by":1,"id":"45334","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"45334"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00045334","sets":["1887:1893","1896:1898:1913:1917"]},"author_link":["474190","474188","474189","474187"],"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1990-08","bibliographicIssueDateType":"Issued"},"bibliographicPageStart":"24","bibliographicVolumeNumber":"1075T","bibliographic_titles":[{},{"bibliographic_title":"Technical Report of National Aerospace Laboratory TR-1075T","bibliographic_titleLang":"en"}]}]},"item_3_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"翼型の後縁の形状や厚さは翼型の抵抗と深く関わっている。従来,ポテンシャル方程式,オイラー方程式による翼型解析では後縁は鋭い厚さのないものとして取り扱われてきた。そして後縁では流れが後縁から滑らかに出るといういわゆるKutta条件が適用される。時間平均NS解析法においても,翼弦方向の格子間隔はオイラー解析と同じ程度であり,後縁付近の流れはマクロに捕えているのが普通である。しかしこれでは後縁付近の流れの詳細は解らず,抵抗削減の手掛かりも掴み難い。そこで著者は高性能な遷音速翼型設計の手掛かりを得る目的で,Baldwin-Lomax乱流モデルによる2次元時間平均NS解析法を用いて鋭い後縁をもつNACA0012と遷音速翼型の遷音速流れについて予備的な解析を行なった。通常の解析法では厚さゼロの鋭い後縁とみなされる領域に微細な格子を集中させて後縁の流れ場を詳細に解析する。解析は3種類の後縁厚さを持つNACA0012:カスプ型鋭い後縁,標準の後縁厚あり,1％後縁厚あり,について行い,通常の解析法の扱いの結果と比較した。遷音速翼型については0.5％後縁厚の15％厚翼型について解析した。その結果,鋭い厚みのある後縁からはKarman渦に似た非定常な渦の放出が見られ,後縁付近の表面圧力が渦放出の為に振動することが示された。そして振動現象の周期,振幅は翼型,後縁厚さ等に関係し,このような鈍い後縁ではKutta条件は必ずしも成立しないことが明らかになった。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"A preliminary analysis of flow about the blung trailing edge of the NACA 0012 and supercritical airfoils in transonic speed was made utilizing a 2-D time-averaged Navier-Stokes code with the turbulence model of Baldwin and Lomax. A very fine mesh distribution was focused at the trailing edge region which conventional codes treat as a sharp trailing edge with zero thickness. Computation was made for the NACA 0012 airfoil with three kinds of trailing edge thicknesses, cusp-type sharp, standard and 1％ thickness and was compared with the result of a conventionally-treated trailing edge. Fifteen percent thickness supercritical airfoil with trailing edge thickness of 0.5％ was also analyzed. It was found that a vortex shedding similar to the Karman vortices is formed and surface pressure near the trailing edge shows unsteady oscillation due to the vortices. The magnitude and periodicity of the oscillation is governed by the bluntness. Also, it was shown that the ′Kutta condition′ is not necessarily satisfied for the blunt trailing edge.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: NALTR1075000","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-1075T","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力性能部"},{"subitem_text_value":"航空宇宙技術研究所新型航空機研究グループ"}]},"item_3_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"Aircraft Aerodynamics Division, National Aerospace Laboratory(NAL)"},{"subitem_text_language":"en","subitem_text_value":"Advanced Aircraft Research Group, 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":"神谷, 信彦"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"HIROSE, Naoki","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"KAMIYA, Nobuhiko","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":"naltr1075t.pdf","filesize":[{"value":"1.8 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"naltr1075t.pdf","url":"https://jaxa.repo.nii.ac.jp/record/45334/files/naltr1075t.pdf"},"version_id":"280384c4-a7ef-4339-9cfb-37f8088d8730"}]},"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":"Blunt Trailing Edge Analysis of Supercritical Airfoils by a Navier-Stokes Code","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"Blunt Trailing Edge Analysis of Supercritical Airfoils by a Navier-Stokes Code","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":"45334","relation_version_is_last":true,"title":["Blunt Trailing Edge Analysis of Supercritical Airfoils by a Navier-Stokes Code"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T21:41:13.424703+00:00"}