{"created":"2023-06-20T15:08:17.222909+00:00","id":37697,"links":{},"metadata":{"_buckets":{"deposit":"80036039-6e17-4893-8c9b-fef6b2c85f46"},"_deposit":{"created_by":1,"id":"37697","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"37697"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00037697","sets":["1887:1891","1896:1898:1913:1915"]},"author_link":["482553","482552","482550","482551"],"item_5_alternative_title_1":{"attribute_name":"その他のタイトル","attribute_value_mlt":[{"subitem_alternative_title":"ナビア・ストークス解析を用いたヘリコプタ・ロータ・ブレード用第3世代高性能翼型の設計"}]},"item_5_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1992-12","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"62","bibliographicPageStart":"57","bibliographicVolumeNumber":"19","bibliographic_titles":[{"bibliographic_title":"航空宇宙技術研究所特別資料: 第10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 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 10-12 Jun. 1992 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 10-12 Jun. 1992 Tokyo Japan","subitem_description_type":"Other"}]},"item_5_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"近年におけるヘリコプタの性能の進歩は著しく、実験ヘリコプタの間では200kt以上の最高速をもつものも稀でない。そのような高性能性は、先進的な翼型を含むロータ空気力学の進歩に負うところが大きい。また、計算流体力学(CFD)およびスーパーコンピュータにおける最近の進歩は著しく、粘性や渦の効果が支配的な最大揚力前後の領域まで翼型の性能を予測することができる。このような中で、富士重工においては社内の基礎研究として先進的翼型の設計に関する研究が行われており、2次元ナビエ・ストークス方程式コードを設計法に組み込むことにより最大揚力の有効かつ正確な予測を可能にした。手始めとして、実際的な設計目標、つまりボーイング社ヘリコプタの第3世代翼型VR-12からVR-15までと同等の性能をもつ翼型形状の確立、を設定した。設計に入る前に、翼型の最大揚力は前縁形状に強く依存する事実から、前縁厚さとキャンバについてのパラメトリックスタディを行った。実際上の設計では、このパラメトリックスタディに基いて最適な前縁厚さとキャンバの組み合せを選んだ。次に、形状、特に前縁まわりのそれを、他の性能を損うことなく最大揚力を大きくするため前縁負圧を穏かなものとするよう調整した。さらに、設計点以外の全体的な特性を遷音速マッハ数に至るまで調べた。このような設計で得られた翼型はU896Hと名付けられ、翼厚比が10％で前縁における最適化のためのキャンバ以外は対称形の断面をもっている。風洞試験の結果は、この翼型が期待されたような第3世代翼型として十分に高い最大揚力および抵抗発散マッハ数をもつことを示す。","subitem_description_type":"Abstract"}]},"item_5_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"Recent progress in the performance of helicopters has been so remarkable that maximum speed of over 200 knot is not uncommon among experimental helicopters. Such high performance owes much to the progress in rotor aerodynamics including advanced airfoils. Also remarkable has been the recent progress in Computational Fluid Dynamics (CFD) and super computers. Which makes it possible to predict airfoil performance accurately up to and beyond maximum lift where viscous and vortical effects prevail. First of all, a practical design target was settled, that is to obtain airfoil shapes with comparable performance to that of Boeing Helicopter's third-generation airfoils VR-12 through VR-15. Prior to the design a parametric study on leading edge thickness and camber was carried out upon the fact that maximum lift of airfoils depends much upon leading edge shape. In practical design an optimal combination of leading edge thickness and cambar was selected upon the parametric study. Then, the shape especially around the leading edge was successively refined by relaxing leading edge pressure peak to realize much higher maximum lift without spoiling other performance. Last of all off-design and overall characteristics were checked up to transonic Mach numbers. The airfoil U896H thus designed, has thickness over chord ratio of 0.10 and has symmetric section shape except for the optimized cambar around the leading edge. Wind tunnel results of the airfoil showed high maximum lift and high drag divergence Mach number as expected and enough to be among third-generation airfoils.","subitem_description_type":"Other"}]},"item_5_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0004168011","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-19","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":"富士重工業"},{"subitem_text_value":"富士重工業"}]},"item_5_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"Fuji Heavy Industries Ltd"},{"subitem_text_language":"en","subitem_text_value":"Fuji Heavy Industries Ltd"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"中館, 正顯"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"小生方, 正裕"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Nakadate, Masaaki","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Obukata, Masahiro","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":"nalsp0019011.pdf","filesize":[{"value":"499.0 kB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"nalsp0019011.pdf","url":"https://jaxa.repo.nii.ac.jp/record/37697/files/nalsp0019011.pdf"},"version_id":"314272ef-d209-4d18-8619-ac97e82de1ed"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"高速翼型","subitem_subject_scheme":"Other"},{"subitem_subject":"高揚力翼型","subitem_subject_scheme":"Other"},{"subitem_subject":"ヘリコプタロータブレード","subitem_subject_scheme":"Other"},{"subitem_subject":"ロータ空気力学","subitem_subject_scheme":"Other"},{"subitem_subject":"翼前縁形状","subitem_subject_scheme":"Other"},{"subitem_subject":"翼厚分布","subitem_subject_scheme":"Other"},{"subitem_subject":"翼型形状パラメトリックスタディ","subitem_subject_scheme":"Other"},{"subitem_subject":"翼型形状最適化","subitem_subject_scheme":"Other"},{"subitem_subject":"遷音速空力特性","subitem_subject_scheme":"Other"},{"subitem_subject":"空力設計ツール","subitem_subject_scheme":"Other"},{"subitem_subject":"CFD利用","subitem_subject_scheme":"Other"},{"subitem_subject":"計算空気力学利用","subitem_subject_scheme":"Other"},{"subitem_subject":"粘性効果予測","subitem_subject_scheme":"Other"},{"subitem_subject":"高揚力空気力学","subitem_subject_scheme":"Other"},{"subitem_subject":"抵抗発散マッハ数","subitem_subject_scheme":"Other"},{"subitem_subject":"high speed airfoil","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"high lift airfoil","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"helicopter rotor blade","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"rotor aerodynamics","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"wing leading edge shape","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"airfoil thickness distribution","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"airfoil shape parametric study","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"airfoil shape optimization","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"transonic aerodynamic characteristic","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"aerodynamic design tool","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"CFD utilization","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"computational fluid dynamics utilization","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"viscous effect prediction","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"high lift aerodynamics","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"drag divergent Mach number","subitem_subject_language":"en","subitem_subject_scheme":"Other"}]},"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":"conference paper","resourceuri":"http://purl.org/coar/resource_type/c_5794"}]},"item_title":"A design of third-generation airfoils for helicopter rotor blades using Navier-Stokes","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"A design of third-generation airfoils for helicopter rotor blades using Navier-Stokes","subitem_title_language":"en"}]},"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":"37697","relation_version_is_last":true,"title":["A design of third-generation airfoils for helicopter rotor blades using Navier-Stokes"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T21:14:43.063165+00:00"}