{"created":"2023-06-20T15:12:43.920674+00:00","id":42601,"links":{},"metadata":{"_buckets":{"deposit":"ed304437-c412-4adc-941e-076e429ceefb"},"_deposit":{"created_by":1,"id":"42601","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"42601"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00042601","sets":["1887:1893","1896:1898:1913:1917"]},"author_link":["459265","459274","459268","459270","459276","459272","459271","459267","459275","459263","459266","459273","459264","459269"],"item_3_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Experimental and numerical validation of the natural laminar flow wing of non-powered experimental airplane for supersonic transport"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"2002-02","bibliographicIssueDateType":"Issued"},"bibliographicVolumeNumber":"1437","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":"小型超音速ロケット実験機の自然層流翼の遷移特性をホットフィルムと赤外線カメラを用いて計測した。高後退翼の遷移を支配する横流れ不安定の発達を抑制するために、自然層流翼では前縁付近の急加速領域を狭くすることで横流れ速度成分を抑えている。本翼の遷移Reynolds数は単位Reynolds数に依存せず、設計迎角(α=2deg)において70％半翼幅位置における遷移Reynolds数は0.8 x 10(exp 6)であることがわかった。線形安定解析結果から本翼を支配する不安定性はTollmien-Schlichting不安定性であり、横流れ不安定は設計通り抑制されていることがわかった。表面粗さと主流乱れの影響を考慮すると、飛行試験 M=2、α=2deg (設計迎角)において70％半翼幅位置の遷移位置は約50％翼拡張と推定された。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"Transition characteristics on the natural laminar flow wing of a nonpowered scaled supersonic experimental airplane was measured by hot film sensors and infrared camera in two supersonic wind tunnels at Mach 2. In order to suppress the growth of crossflow instability which dominates the transition on highly swept wings, the pressure falls very rapidly in the vicinity of leading edge of the wing, so as to minimize the crossflow velocity components. From test results, the unit Reynolds number had no effect on the transition Reynolds number of the wing. The transition Reynolds number was 0.8 million at 70 percent semispanwise location at Mach 2 at the angle of attack of 2 deg. Tollmien-Schlichting instability dominates the transition and crossflow instability was found to be suppressed on the wing. Considering the influence of surface roughness and free-stream turbulence, the transition at 70 percent semi-spanwise position at Mach at the angle of attack of 2 deg in flight is estimated to be located at 50 percent chordwise position.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0032998000","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-1437","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 流体科学研究センター"},{"subitem_text_value":"航空宇宙技術研究所 流体科学研究センター"},{"subitem_text_value":"航空宇宙技術研究所 流体科学研究センター"},{"subitem_text_value":"航空宇宙技術研究所 流体科学研究センター"},{"subitem_text_value":"航空宇宙技術研究所 次世代航空プロジェクト推進センター"},{"subitem_text_value":"航空宇宙技術研究所 次世代航空プロジェクト推進センター"},{"subitem_text_value":"航空宇宙技術研究所"}]},"item_3_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Fluid Science Research Center"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Fluid Science Research Center"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Fluid Science Research Center"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Fluid Science Research Center"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Next Generation SST Project Center"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Next Generation SST Project Center"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"杉浦, 裕樹"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"高木, 正平"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"徳川, 直子"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"西沢, 啓"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"吉田, 憲司"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"野口, 正芳"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"上田, 良稲"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Sugiura, Hiroki","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Takagi, Shohei","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Tokugawa, Naoko","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Nishizawa, Akira","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Yoshida, Kenji","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Noguchi, Masayoshi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Ueda, Yoshine","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":"2020-01-28"}],"displaytype":"detail","filename":"naltr0001437.pdf","filesize":[{"value":"357.5 kB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"naltr0001437.pdf","url":"https://jaxa.repo.nii.ac.jp/record/42601/files/naltr0001437.pdf"},"version_id":"37fed0af-68cc-4808-91d8-2de9787e6d6b"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"超音速輸送","subitem_subject_scheme":"Other"},{"subitem_subject":"実験航空機","subitem_subject_scheme":"Other"},{"subitem_subject":"層流","subitem_subject_scheme":"Other"},{"subitem_subject":"境界層遷移","subitem_subject_scheme":"Other"},{"subitem_subject":"熱フィルム風速計","subitem_subject_scheme":"Other"},{"subitem_subject":"赤外線写真","subitem_subject_scheme":"Other"},{"subitem_subject":"超音速風洞","subitem_subject_scheme":"Other"},{"subitem_subject":"supersonic transport","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"research aircraft","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"laminar flow","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"boundary layer transition","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"hot film anemometer","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"infrared photography","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"supersonic wind tunnel","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":"小型超音速ロケット実験機の自然層流翼の風洞試験および解析による検証","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"小型超音速ロケット実験機の自然層流翼の風洞試験および解析による検証"}]},"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":"42601","relation_version_is_last":true,"title":["小型超音速ロケット実験機の自然層流翼の風洞試験および解析による検証"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T22:23:17.191380+00:00"}