{"created":"2023-06-20T14:35:54.199469+00:00","id":2190,"links":{},"metadata":{"_buckets":{"deposit":"2c738fbd-4907-480e-9da5-f1bc3a5403a1"},"_deposit":{"created_by":1,"id":"2190","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"2190"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00002190","sets":["1887:1893","9:10:200:211"]},"author_link":["4183","4185","4186","4180","4181","4187","4188","4189","4182","4184"],"item_3_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Demonstration of aerodynamic design technologies on supersonic experimental airplane (NEXST-1) by flight test"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"2007-03-30","bibliographicIssueDateType":"Issued"},"bibliographicVolumeNumber":"JAXA-RR-06-041","bibliographic_titles":[{"bibliographic_title":"宇宙航空研究開発機構研究開発報告"},{"bibliographic_title":"JAXA Research and Development Report","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(NEXST-1: National EXperimental Supersonic Transport-1)の第2回目の飛行実験を2005年10月に豪州ウーメラ実験場において行った。飛行実験では予定していた全てのシーケンスを正常に実施し、貴重な飛行実験データを健全に取得することができた。その中で、空力データは空力設計コンセプトを検証する上で重要な計測項目のひとつである。本稿では飛行実験で得られた空力データを評価し、空力設計の妥当性について検討した結果を報告する。具体的には、飛行実験により計測された空力データをCFD(Computational Fluid Dynamics)解析結果と比較し、抵抗低減コンセプトを取り込んだNEXST-1の空力設計に対する妥当性を検証することができた。これは機体まわりの表面静圧分布がCFD解析と概ね一致していること、胴体や主翼まわりの表面静圧分布の分析からワープ主翼、エーリアルール胴体の設計コンセプトの妥当性が確認できたこと、さらに主翼上面の圧力分布に関して自然層流翼設計に用いた目標静圧分布と良好な一致が得られたことによる。また気流乱れの小さい飛行実験条件下で、主翼上面や前胴まわりの境界層遷移データの取得に成功し、その遷移計測結果から設計点において主翼上面の境界層遷移位置がもっとも後退していることが明らかになり、自然層流翼設計の妥当性が完全に確認された。さらにその遷移計測結果を数値予測結果と定量的に比較し、境界層遷移予測ツールの精度向上に役立つ知見も得られた。特に設計点における抵抗係数の特性は、飛行実験結果とCFD解析結果で良好な一致が示され、これにより超音速巡航時の設計点における抵抗低減コンセプトの妥当性が定量的に検証された。しかしながら、表面静圧分布や空気力特性の1部の飛行実験データにはまだCFD解析結果や風洞試験結果との不一致が見られ、現在もその原因については検討を続けている段階にある。最後に今回の飛行実験により得られた技術を適用して想定実機スケールのSST(SuperSonic Transport)形状の設計を行い、実機スケールにおいて巡航マッハ数と設計揚力で13％の揚抗比改善効果の得られることを確認した。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"Flight test of a supersonic experimental airplane was performed by Japan Aerospace Exploration Agency to improve advanced aerodynamic design technologies for the next generation SST (SuperSonic Transport). The experimental airplane was designed to reduce the drag on a supersonic cruise condition. Surface pressure distributions, boundary layer transition locations and aerodynamic forces in the flight test were obtained to validate the aerodynamic design concepts. The flight test results were evaluated by comparing with the prediction results obtained by CFD (Computational Fluid Dynamics) based optimum design tools. The flight test results were confirmed to be corresponding to the CFD results. Therefore, the aerodynamic design concepts for drag reduction were demonstrated qualitatively and quantitatively by the NEXST-1 (National EXperimental Supersonic Transport-1) flight test.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0063727000","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: JAXA-RR-06-041","subitem_description_type":"Other"}]},"item_3_publisher_8":{"attribute_name":"出版者","attribute_value_mlt":[{"subitem_publisher":"宇宙航空研究開発機構"}]},"item_3_publisher_9":{"attribute_name":"出版者（英）","attribute_value_mlt":[{"subitem_publisher":"Japan Aerospace Exploration Agency (JAXA)"}]},"item_3_source_id_21":{"attribute_name":"ISSN","attribute_value_mlt":[{"subitem_source_identifier":"1349-1113","subitem_source_identifier_type":"ISSN"}]},"item_3_source_id_24":{"attribute_name":"書誌レコードID","attribute_value_mlt":[{"subitem_source_identifier":"AA1192675X","subitem_source_identifier_type":"NCID"}]},"item_3_text_6":{"attribute_name":"著者所属","attribute_value_mlt":[{"subitem_text_value":"宇宙航空研究開発機構 航空プログラムグループ　超音速機チーム"},{"subitem_text_value":"宇宙航空研究開発機構 総合技術研究本部　空気力学研究グループ"},{"subitem_text_value":"宇宙航空研究開発機構 航空プログラムグループ　超音速機チーム"},{"subitem_text_value":"三向ソフトウェア開発"},{"subitem_text_value":"宇宙航空研究開発機構 航空プログラムグループ　超音速機チーム"}]},"item_3_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"Japan Aerospace Exploration Agency Supersonic Transport Team, Aviation Program Group"},{"subitem_text_language":"en","subitem_text_value":"Japan Aerospace Exploration Agency Aerodynamics Research Group, Institute of Aerospace Technology"},{"subitem_text_language":"en","subitem_text_value":"Japan Aerospace Exploration Agency Supersonic Transport Team, Aviation Program Group"},{"subitem_text_language":"en","subitem_text_value":"Sanko Software Ltd."},{"subitem_text_language":"en","subitem_text_value":"Japan Aerospace Exploration Agency Supersonic Transport Team, Aviation Program Group"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"Kwak, Dong-Youn"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"徳川, 直子"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"吉田, 憲司"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"石川, 敬掲"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"野口, 正芳"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Kwak, Dong-Youn","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Tokugawa, Naoko","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Yoshida, Kenji","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Ishikawa, Akihiro","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Noguchi, Masayoshi","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":"2020-01-15"}],"displaytype":"detail","filename":"63727000.pdf","filesize":[{"value":"9.9 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"63727000.pdf","url":"https://jaxa.repo.nii.ac.jp/record/2190/files/63727000.pdf"},"version_id":"9a338b0c-d0ab-4d51-a1db-80c4eb854355"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"超音速機","subitem_subject_scheme":"Other"},{"subitem_subject":"NEXST-1","subitem_subject_scheme":"Other"},{"subitem_subject":"航空機設計","subitem_subject_scheme":"Other"},{"subitem_subject":"空力設計","subitem_subject_scheme":"Other"},{"subitem_subject":"超音速飛行","subitem_subject_scheme":"Other"},{"subitem_subject":"圧力分布","subitem_subject_scheme":"Other"},{"subitem_subject":"境界層遷移","subitem_subject_scheme":"Other"},{"subitem_subject":"飛行試験機","subitem_subject_scheme":"Other"},{"subitem_subject":"飛行試験","subitem_subject_scheme":"Other"},{"subitem_subject":"計算流体力学","subitem_subject_scheme":"Other"},{"subitem_subject":"風洞試験","subitem_subject_scheme":"Other"},{"subitem_subject":"設計最適化","subitem_subject_scheme":"Other"},{"subitem_subject":"supersonic aircraft","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"NEXST-1","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"aircraft design","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"aerodynamic design","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"supersonic flight","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"pressure distribution","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"boundary layer transition","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"flight test vehicle","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"flight test","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"computational fluid dynamics","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"wind tunnel test","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"design optimization","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":"小型超音速実験機(NEXST-1)飛行実験による空力設計の検証","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"小型超音速実験機(NEXST-1)飛行実験による空力設計の検証"}]},"item_type_id":"3","owner":"1","path":["211","1893"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"2190","relation_version_is_last":true,"title":["小型超音速実験機(NEXST-1)飛行実験による空力設計の検証"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-21T09:26:56.526778+00:00"}