{"created":"2023-06-20T15:11:29.285807+00:00","id":41156,"links":{},"metadata":{"_buckets":{"deposit":"d89c9887-4669-4bc1-bed2-a4f111330bdc"},"_deposit":{"created_by":1,"id":"41156","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"41156"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00041156","sets":["1887:1893","1896:1898:1913:1917"]},"author_link":["450824","450822","450823","450820","450821","450818","450825","450819"],"item_3_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Low-speed wind tunnel tests on a joined-wing aircraft model with various upper-fin"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1992-07","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"25","bibliographicPageStart":"1","bibliographicVolumeNumber":"1169","bibliographic_titles":[{"bibliographic_title":"航空宇宙技術研究所報告"},{"bibliographic_title":"Technical Report of National Aerospace Laboratory","bibliographic_titleLang":"en"}]}]},"item_3_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"主翼に後退角と上反角をつけ、水平尾翼に前進角と下反角をつけて両者を結合した菱型結合翼機は、その構造的な特徴から剛性が高い、誘導抵抗が小さい、直接揚力、横力制御が可能である、などの利点を有するといわれている。菱型結合翼機は重心を主翼と水平尾翼の間におき、両者の舵面を適度に組み合わせることにより直接揚力、横力制御が可能であるが、各舵面の操舵余裕や操舵配分が懸念されることがわかった。このため、より大きな横力を発生させる目的で後縁舵面付き上翼(主翼上面にたてた小翼)を取り付けることにした。しかし、この上翼は全機の空力特性にも影響を与えることが考えられるので、効率がよいといわれる主翼翼幅の60％位置で結合した菱型結合翼を用いて、形状の異なる4種類の上翼と3か所の取り付け位置とを組み合わせた各形態(内4形態は省略)について6分力測定と流れの可視化試験を行ったので、その結果について報告する。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"Low-speed wind tunnel tests were conducted on a joined-wing aircraft model with various upper-fin (small wing-like surface fitted on the wing or the horizontal tail). The upper-fin was used to enhance direct side-force control capability. In this case, the upper-fin was equipped with a plain flap as a rudder. The effects of upper-fin on the aerodynamic characteristics of a joined-wing aircraft are described. The ratio of the rear to front wing span was selected 0.6 to be said best condition. Four different shaped upper-fins were installed at the three locations on the each wing at 0.6 half span, but four cases were not used. Reynolds number based on the mean aerodynamic chord was (from 6.5 to 6.7) x 10 (exp 5). the angle of attack was varied from zero deg to 25 deg, and the side-slip angle from zero deg to 15 deg. The results indicated that the upper-fin acts like a 'boundary layer fence' and protects wing tip stall when the upper-fin is installed on the wing. On the other hand, however, the upper-fin produced local flow separation over the wing, and this flow separation caused asymmetric lateral and directional characteristics with side-slip angle.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0004186000","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-1169","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 新型航空機研究グループ"},{"subitem_text_value":"航空宇宙技術研究所 新型航空機研究グループ"},{"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":"National Aerospace Laboratory Advanced Aircraft Research Group"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Advanced Aircraft Research Group"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Advanced Aircraft Research Group"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"岩崎, 昭人"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"藤田, 敏美"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"藤枝, 郭俊"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"滝澤, 直人"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Iwasaki, Akihito","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Fujita, Toshimi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Fujieda, Hirotoshi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Takizawa, Naoto","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":"2020-01-27"}],"displaytype":"detail","filename":"naltr01169.pdf","filesize":[{"value":"6.1 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"naltr01169.pdf","url":"https://jaxa.repo.nii.ac.jp/record/41156/files/naltr01169.pdf"},"version_id":"fc17edc0-579a-46fe-8cdc-842a3e9fcd14"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"結合翼","subitem_subject_scheme":"Other"},{"subitem_subject":"先進航空機形態","subitem_subject_scheme":"Other"},{"subitem_subject":"省エネルギー型航空機","subitem_subject_scheme":"Other"},{"subitem_subject":"新世代航空機","subitem_subject_scheme":"Other"},{"subitem_subject":"後退翼","subitem_subject_scheme":"Other"},{"subitem_subject":"前進翼","subitem_subject_scheme":"Other"},{"subitem_subject":"菱形平面形翼","subitem_subject_scheme":"Other"},{"subitem_subject":"低速風洞試験","subitem_subject_scheme":"Other"},{"subitem_subject":"空力特性","subitem_subject_scheme":"Other"},{"subitem_subject":"垂直フィン","subitem_subject_scheme":"Other"},{"subitem_subject":"直接横力制御","subitem_subject_scheme":"Other"},{"subitem_subject":"舵面効き","subitem_subject_scheme":"Other"},{"subitem_subject":"横力発生舵面","subitem_subject_scheme":"Other"},{"subitem_subject":"誘導抵抗減少","subitem_subject_scheme":"Other"},{"subitem_subject":"流れの可視化","subitem_subject_scheme":"Other"},{"subitem_subject":"joined wing","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"advanced aircraft configuration","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"energy efficient airplane","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"new generation aircraft","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"sweptback ing","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"sweptforward wing","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"rhombic planform wing","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"low speed wind tunnel test","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"aerodynamic characteristic","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"vertical fin","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"direct side force control","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"control surface effectiveness","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"side force generator","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"induced drag reduction","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"flow visualization","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":"technical report","resourceuri":"http://purl.org/coar/resource_type/c_18gh"}]},"item_title":"菱形結合翼機(上翼付き)の低速風洞実験","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"菱形結合翼機(上翼付き)の低速風洞実験"}]},"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":"41156","relation_version_is_last":true,"title":["菱形結合翼機(上翼付き)の低速風洞実験"],"weko_creator_id":"1","weko_shared_id":1},"updated":"2023-06-20T19:13:00.330455+00:00"}