Transition measurement on the natural laminar flow wing of the non-powered experimental airplane for supersonic transport

Material type: 文書・図像類

Author: 杉浦, 裕樹ほか

Publisher: 航空宇宙技術研究所

Publication date: 2000-12

Material Format: Digital

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Note (General)：: 航空宇宙技術研究所 27-29 Sept.2000 東京日本National Aerospace Laboratory 27-29 Sept.2000 Tokyo Japan超音速輸送機を目的とした無推力実験機の自然層流翼上の遷移測定をマッハ数2.0と1.2で行った。翼弦沿いに設置した熱フィルム流...

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Material Type: 文書・図像類
Title: Transition measurement on the natural laminar flow wing of the non-powered experimental airplane for supersonic transport
Author/Editor: 杉浦, 裕樹
吉田, 憲司
徳川, 直子
高木, 正平
西沢, 啓
Sugiura, Hiroki
Yoshida, Kenji
Tokugawa, Naoko
Takagi, Shohei
Nishizawa, Akira
Author Heading: 杉浦, 裕樹
吉田, 憲司
徳川, 直子
高木, 正平
西沢, 啓
Sugiura, Hiroki
Yoshida, Kenji
Tokugawa, Naoko
Takagi, Shohei
Nishizawa, Akira
Publication, Distribution, etc.: 航空宇宙技術研究所
Publication Date: 2000-12
Publication Date (W3CDTF): 2000-12
Alternative Title: 超音速輸送機向け無推力実験機の自然層流翼上の遷移測定
Periodical title: 航空宇宙技術研究所特別資料 = Special Publication of National Aerospace Laboratory
No. or year of volume/issue: 48T
Volume: 48T
Pages: 51-54
ISSN (Periodical Title): ISSN : 0289-260X
Text Language Code: eng
Subject Heading: 超音速輸送機
無推力実験機
自然層流翼
乱流境界層
遷移点
翼弦
直交流不安定性
最適圧力分布
圧縮性境界層
遷移測定
supersonic transport
nonpowered experimental airplane
natural laminar flow wing
turbulent boundary layer
transition point
wing chord
crossflow instability
optimum pressure distribution
compressible boundary layer
transition measurement
Target Audience: 一般
Note (General): 航空宇宙技術研究所 27-29 Sept.2000 東京日本
National Aerospace Laboratory 27-29 Sept.2000 Tokyo Japan
超音速輸送機を目的とした無推力実験機の自然層流翼上の遷移測定をマッハ数2.0と1.2で行った。翼弦沿いに設置した熱フィルム流速計に対する出力信号の振幅中の摂動増加が層流から乱流境界層への遷移を示す。熱フィルム流速計およびPreston管による測定結果は遷移点が翼の半弦の下流に位置していることを明らかにした。
Transition measurement on the natural laminar flow wing of non-powered experimental airplane for supersonic transport was conducted at Mach 2.0 and 1.2. Increase of perturbation in amplitude of output signals for hot-films placed along the wing chord indicates transition from laminar to turbulent boundary layer. Results by hot-film and Preston tubes proved that transition point is located downstream of the half chord of the wing.
資料番号: AA0028637019
レポート番号: NAL SP-48T
Access Restrictions: 限定公開
Periodical Title (NCID): AN10097345
https://ci.nii.ac.jp/ncid/AN10097345
Data Provider (Database): 国立情報学研究所 : 学術機関リポジトリデータベース（IRDB）（機関リポジトリ）
https://irdb.nii.ac.jp
Original Data Provider (Database): 宇宙航空研究開発機構 : 宇宙航空研究開発機構リポジトリ