衝撃波を伴わない遷音速翼型の実験

Material type: 文書・図像類

Author: 中村, 正義ほか

Publisher: 航空宇宙技術研究所

Publication date: 1983-10

Material Format: Digital

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Note (General)：: An experiment was carried out on transonic flows over an airfoil which was partially modified from an arbitrary airfoil. The modification was made to ...

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Material Type: 文書・図像類
Title: 衝撃波を伴わない遷音速翼型の実験
Author/Editor: 中村, 正義
鈴木, 弘一
中村, 正剛
白井, 正孝
NAKAMURA, Masayoshi
SUZUKI, Koichi
NAKAMURA, Seigou
SHIRAI, Masataka
Author Heading: 中村, 正義
鈴木, 弘一
中村, 正剛
白井, 正孝
NAKAMURA, Masayoshi
SUZUKI, Koichi
NAKAMURA, Seigou
SHIRAI, Masataka
Publication, Distribution, etc.: 航空宇宙技術研究所
Publication Date: 1983-10
Publication Date (W3CDTF): 1983-10
Alternative Title: Experiment of a Schockless Transonic Airfoil
Periodical title: 航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-783
No. or year of volume/issue: 783
Volume: 783
Pages: 8-
ISSN (Periodical Title): ISSN : 0389-4010
Text Language Code: jpn
Target Audience: 一般
Note (General): An experiment was carried out on transonic flows over an airfoil which was partially modified from an arbitrary airfoil. The modification was made to satisfy the shockless condition which predicted on NAL TR-602, TR-602T. Static pressure were measured at 88 points on the airfoil surface, when the test Mach number was 0.5～0.8, the test angle of attack was 0deg～4deg and the Reynolds number was 4.0～4.6×10(exp 6). A schockless transonic flow was observed under a test condition close to the design condition. The supersonic region extends from 0.3％ to 63％ of airfoil chord length and the local maximum Mach number is 1.36. The result of this experiment supports the artificial flow method for obtaining shockless transonic airfoils which are partially modified from an arbitrary airfoil.
資料番号: NALTR0783000
レポート番号: NAL TR-783
Access Restrictions: 限定公開
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