Flow Quality of NAL Two-Dimensional Transonic Wind Tunnel Part I Mach Number Distributions,Flow Angularities and Preliminary Study of Side Wall Boundary Layer Suction

Material type: 文書・図像類

Author: 榊原, 盛三ほか

Publisher: 航空宇宙技術研究所

Publication date: 1982-01

Material Format: Digital

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Note (General)：: Experimental data on the flow quality of the NAL two-dimensional transonic wind tunnel are presented. Mach number distributions on the test section ax...

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Material Type: 文書・図像類
Title: Flow Quality of NAL Two-Dimensional Transonic Wind Tunnel Part I Mach Number Distributions,Flow Angularities and Preliminary Study of Side Wall Boundary Layer Suction
Author/Editor: 榊原, 盛三
高島, 一明
三輪, 等
小国, 保男
佐藤, 衛
神田, 宏
SAKAKIBARA, Seizo
TAKASHIMA, Kazuaki
MIWA, Hitoshi
OGUNI, Yasuo
SATO, Mamoru
KANDA, Hiroshi
Author Heading: 榊原, 盛三
高島, 一明
三輪, 等
小国, 保男
佐藤, 衛
神田, 宏
SAKAKIBARA, Seizo
TAKASHIMA, Kazuaki
MIWA, Hitoshi
OGUNI, Yasuo
SATO, Mamoru
KANDA, Hiroshi
Publication, Distribution, etc.: 航空宇宙技術研究所
Publication Date: 1982-01
Publication Date (W3CDTF): 1982-01
Alternative Title: 航技研二次元風胴の気流特性について(I)-マッハ数分布の気流偏角および側壁からの境界層吸込予備試験-
Periodical title: 航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-693
No. or year of volume/issue: 693
Volume: 693
Pages: 26-
ISSN (Periodical Title): ISSN : 0389-4010
Text Language Code: eng
Target Audience: 一般
Note (General): Experimental data on the flow quality of the NAL two-dimensional transonic wind tunnel are presented. Mach number distributions on the test section axis show good uniformity which is characterised by the two-sigma(standard deviation) values of 0.0003 to 0.001 for a range of Mach numbers from 0.4 to 1.0 Flow angularities, which were measured by using a wing model with a symmetrical cross section, remained within 0.04 degree for Mach numbers from 0.2 to 0.8. Side wall boundary layer suction was applied through a pair of porous plates. The variation of aerodynamic properties of the model due to the suction mass flow rate change is presented with a brief discussion. Two-dimensionality of the flow over the wing span is expected to be improved by applying the appropriate suction rate, which depends on the Mach number, Reynolds number and lift coefficient.
資料番号: NALTR0693000
レポート番号: NAL TR-693
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