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SST実験機に関する幾つかの遷移計測
https://jaxa.repo.nii.ac.jp/records/41361
https://jaxa.repo.nii.ac.jp/records/413618ba64fbf-a41b-4699-9451-1158a3d97d0e
名前 / ファイル | ライセンス | アクション |
---|---|---|
nalsp0047001.pdf (1.6 MB)
|
|
Item type | テクニカルレポート / Technical Report(1) | |||||
---|---|---|---|---|---|---|
公開日 | 2015-03-26 | |||||
タイトル | ||||||
タイトル | SST実験機に関する幾つかの遷移計測 | |||||
言語 | ||||||
言語 | jpn | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | SST実験機 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 超音速輸送機 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 境界層遷移 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 遷移計測 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 超音速流 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 飛行試験 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 自然層流翼 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | CFD手法 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 数値流体力学 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 遷移過程 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | Tollmien-Schlichting波 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 前縁 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 超音速風洞 | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | SST experimental airplane | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | supersonic transport | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | boundary layer transition | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | transition measurement | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | supersonic flow | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | flight test | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | natural laminar flow wing | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | CFD technique | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | computational fluid dynamics | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | transition process | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Tollmien Schlichting wave | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | leading edge | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | supersonic wind tunnel | |||||
資源タイプ | ||||||
資源タイプ識別子 | http://purl.org/coar/resource_type/c_18gh | |||||
資源タイプ | technical report | |||||
その他のタイトル(英) | ||||||
その他のタイトル | Boundary-layer transition measurements associated with NAL experimental SST project | |||||
著者 |
徳川, 直子
× 徳川, 直子× 高木, 正平× 西沢, 啓× 杉浦, 裕樹× Tokugawa, Naoko× Takagi, Shohei× Nishizawa, Akira× Sugiura, Hiroki |
|||||
著者所属 | ||||||
航空宇宙技術研究所 | ||||||
著者所属 | ||||||
航空宇宙技術研究所 | ||||||
著者所属 | ||||||
航空宇宙技術研究所 | ||||||
著者所属 | ||||||
航空宇宙技術研究所 | ||||||
著者所属(英) | ||||||
en | ||||||
National Aerospace Laboratory | ||||||
著者所属(英) | ||||||
en | ||||||
National Aerospace Laboratory | ||||||
著者所属(英) | ||||||
en | ||||||
National Aerospace Laboratory | ||||||
著者所属(英) | ||||||
en | ||||||
National Aerospace Laboratory | ||||||
出版者 | ||||||
出版者 | 航空宇宙技術研究所 | |||||
出版者(英) | ||||||
出版者 | National Aerospace Laboratory (NAL) | |||||
書誌情報 |
航空宇宙技術研究所特別資料 en : Special Publication of National Aerospace Laboratory 巻 47, p. 1-4, 発行日 2000-12 |
|||||
会議概要(会議名, 開催地, 会期, 主催者等) | ||||||
内容記述タイプ | Other | |||||
内容記述 | 27-28 Sept. 1999 (25th). 27-28 Mar. 2000 (26th) | |||||
会議概要(会議名, 開催地, 会期, 主催者等)(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | 27-28 Sept. 1999 (25th). 27-28 Mar. 2000 (26th) | |||||
抄録 | ||||||
内容記述タイプ | Abstract | |||||
内容記述 | CFD(数値流体力学)手法を用いて自然層流翼に適用することを意図したNALのSST(超音速輸送機)計画に関連して境界層遷移計測を実施した。実験の目的は最先端的な境界層遷移に関するデータベースを構築して翼上の遷移点予測の参考とし、また高度な計測技術を確立して航空機の飛行試験に適用することにある。本論文では、代表的な2つの予備実験の結果を報告した。ひとつはビーチクラフト機を使った飛行試験で、低乱流環境下における遷移過程を把握し、飛行試験の諸課題を明らかにするために実施した。Tollmien-Schlichting波が前縁近傍領域で検出され、スペクトルの振幅分布がSALLY(3次元層流境界層安定性解析)コードを使った数値予測値と非常によく一致したことから、風洞内で行う遷移計測が好結果を得ることが分かった。もうひとつは、超音速風洞内においてSST実験機の半裁模型に対して行った計測である。設計点、すなわち、迎角α=2.7度の時のマッハ数M=2では、層流状態は少なくともX/C=0.5に耐えることが分かった。自然層流翼はSST実験機の飛行試験で実現すると期待されている。 | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Boundary-layer transition measurements have been conducted associated with the NAL SST (Supersonic Transport) project, which is designed to apply natural laminar flow wing using CFD (Computational Fluid Dynamics) technique. The purpose of experiments is to construct the database on boundary-layer transition most advanced which will be referred to predict the transition point on the wings, and to establish high quality measurement techniques, which will be applied to the flight test of the airplane. In this paper, the results of two typical preliminary experiments are introduced. One is flight tests using Beachcraft airplane, which are performed to grasp the transition process under low disturbance environment and to clarify the problems of flight test. Transition measurement as conducted in wind-tunnel was found to be successful, because Tollmien-Schlichting wave is detected at the region near the leading edge, and its amplitude distribution of the spectrum is in very good agreement with the numerical prediction by SALLY (3D laminar boundary layer stability analysis)-code. Another is the measurement on a half-model of SST experimental airplane in a supersonic wind tunnel. At the design point, i.e. Mach number M = 2 at an angle of attack alpha = 2.7 deg, it is found that the laminar state sustained at least to X/C = 0.5. Natural laminar flow wing is expected to realize on the flight test of SST experimental airplane. | |||||
ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 0289-260X | |||||
書誌レコードID | ||||||
収録物識別子タイプ | NCID | |||||
収録物識別子 | AN10097345 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: AA0028636001 | |||||
レポート番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | レポート番号: NAL SP-47 |