{"created":"2023-06-20T15:14:34.489976+00:00","id":44559,"links":{},"metadata":{"_buckets":{"deposit":"f46eb11b-6ed8-4b0c-a6b9-0d37a4fbd41b"},"_deposit":{"created_by":1,"id":"44559","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"44559"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00044559","sets":["1887:1893","1896:1898:1913:1917"]},"author_link":["470064","470066","470073","470067","470070","470069","470071","470072","470068","470065"],"item_3_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Some Effects of Center of Gravity Locations of Added Mass on Transonic Flutter Characteristics of Low Aspect Ratio and Sweptback Thin Cantilever Wing"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1973-03","bibliographicIssueDateType":"Issued"},"bibliographicPageStart":"14","bibliographicVolumeNumber":"314","bibliographic_titles":[{"bibliographic_title":"航空宇宙技術研究所報告"},{"bibliographic_title":"Technical Report of National Aerospace Laboratory TR-314","bibliographic_titleLang":"en"}]}]},"item_3_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"前縁の後退角42.5度，後縁の後退角10度，翼面のアスペクト比1.344およびテーパ比0.336の平面形を有する薄い片持平板翼模型の翼端に，翼面重量の約20％の細長い付加質量を気流方向に取り付けて，その重心位置を前後方向に移動させて，付加質量の重心位置の遷音速フラッタ特性におよぼす影響を，遷音速フラッタ試験設備において，マッハ数0.819～1.192の範囲で実験を行なって調べた。実験結果はフラッタ速度係数，実験フラッタ密度および実験フラッタ速度と二次元非圧縮性非定常空気力を用いた理論計算によるフラッタ速度との比を，それぞれマッハ数の関数として表わしている。フラッタ速度係数で表わした不安定領域は，いずれの重心位置の場合もマッハ数1.03の近傍で最も広く，マッハ数1.03の前後では，マッハ数の増減に対し，増加の場合には急激に減少の場合には緩除に安定領域は広くなる傾向を，また付加質量の重心位置が前方にあるほど安定領域が広いことを示している。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"An experimental investigation of some effects of varied location of added mass at wing tip on transonic flutter characteristics of thin cantilever wings has been conducted in the N.A.L. 60cm×60cm transonic blowdown wind tunnel for flutter testing at Mach number between 0.819 and 1.192. The wings have sweptback angle of 42.5 deg at leading edge and of 10 deg at trailing edge, panel aspect ratio of 1.344 and taper ratio of 0.336. The flutter boundary expressed by the experimental flutter-velocity coefficient is characterized by having maximum values at around Mach number 1.03, and stable region expands by moving forword C.G. location of the added mass.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: NALTR0314000","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-314","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機体第一部"},{"subitem_text_value":"航空宇宙技術研究所機体第一部"},{"subitem_text_value":"元・航空宇宙技術研究所機体第一部"},{"subitem_text_value":"航空宇宙技術研究所機体第一部"},{"subitem_text_value":"元・航空宇宙技術研究所機体第一部"}]},"item_3_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"First Airframe Division, National Aerospace Laboratory(NAL)"},{"subitem_text_language":"en","subitem_text_value":"First Airframe Division, National Aerospace Laboratory(NAL)"},{"subitem_text_language":"en","subitem_text_value":"Former First Airframe Division, National Aerospace Laboratory(NAL)"},{"subitem_text_language":"en","subitem_text_value":"First Airframe Division, National Aerospace Laboratory(NAL)"},{"subitem_text_language":"en","subitem_text_value":"Former First Airframe Division, National Aerospace Laboratory(NAL)"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"中井, 暎一"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"森田, 甫之"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"菊池, 孝男"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"東久保, 正年"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"高橋, 実"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"NAKAI, Eiichi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"MORITA, Toshiyuki","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"KIKUCHI, Takao","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"TOKUBO, Masatoshi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"TAKAHASHI, Minoru","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":"naltr00314.pdf","filesize":[{"value":"947.8 kB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"naltr00314.pdf","url":"https://jaxa.repo.nii.ac.jp/record/44559/files/naltr00314.pdf"},"version_id":"e0856ac4-75c3-4cb4-a5d9-3fa133c39feb"}]},"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":"低アスペクト比後退角平板翼の遷音速フラッタ特性におよぼす翼端付加質量の重心位置の影響","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"低アスペクト比後退角平板翼の遷音速フラッタ特性におよぼす翼端付加質量の重心位置の影響"}]},"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":"44559","relation_version_is_last":true,"title":["低アスペクト比後退角平板翼の遷音速フラッタ特性におよぼす翼端付加質量の重心位置の影響"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T21:54:59.676685+00:00"}