航空宇宙技術研究所2m×2m遷音速風洞の省電力運転法の研究

Material type: 文書・図像類

Author: 白井, 正孝ほか

Publisher: 航空宇宙技術研究所

Publication date: 1984-12

Material Format: Digital

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Note (General)：: In the conventional test procedure using the 2m × 2m transonic wind tunnel of the National Aerospace Laboratory, an auxiliary power unit is operated s...

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Material Type: 文書・図像類
Title: 航空宇宙技術研究所2m×2m遷音速風洞の省電力運転法の研究
Author/Editor: 白井, 正孝
中村, 正剛
鈴木, 正光
小池, 陽
鈴木, 弘一
神谷, 信彦
SHIRAI, Masataka
NAKAMURA, Seigou
SUZUKI, Masamitsu
KOIKE, Akira
SUZUKI, Koichi
KAMIYA, Nobuhiko
Author Heading: 白井, 正孝
中村, 正剛
鈴木, 正光
小池, 陽
鈴木, 弘一
神谷, 信彦
SHIRAI, Masataka
NAKAMURA, Seigou
SUZUKI, Masamitsu
KOIKE, Akira
SUZUKI, Koichi
KAMIYA, Nobuhiko
Publication, Distribution, etc.: 航空宇宙技術研究所
Publication Date: 1984-12
Publication Date (W3CDTF): 1984-12
Alternative Title: On Power Efficient Operation of the 2m × 2m Transonic Wind Tunnel at the National Aerospace Laboratory
Periodical title: 航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-847
No. or year of volume/issue: 847
Volume: 847
Pages: 22-
ISSN (Periodical Title): ISSN : 0389-4010
Text Language Code: jpn
Target Audience: 一般
Note (General): In the conventional test procedure using the 2m × 2m transonic wind tunnel of the National Aerospace Laboratory, an auxiliary power unit is operated synergistically for Mach numbers near and above unity in order to establish the desired Mach number at the test section by suction through the perforated test section walls. This power unit consumes a considerable amount of electricity (a maximum of 12000kW). Therefore, as part of the research to explore the possibility of saving energy in wind tunnel operation, an investigation is made here as to what extent the test Mach number can be increased without the use of the auxiliary power unit. It is found that a Mach number of 1.06 is attained by adequately adjusting several geometric parameters such as diverging angle of the side walls of the test section, opening width of the diffuser flaps, width of the second throat and the flexible nozzle setting. Electric power of 7800kW can be saved at Mach number 1 by using this procedure compared with the conventional procedure in which an auxiliary fan is used. Mach number distributions at the test section are found to be little influenced by these adjustments.
資料番号: NALTR0847000
レポート番号: NAL TR-847
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