@techreport{oai:jaxa.repo.nii.ac.jp:00045105,
 author = {白井, 正孝 and 中村, 正剛 and 鈴木, 正光 and 小池, 陽 and 鈴木, 弘一 and 神谷, 信彦 and SHIRAI, Masataka and NAKAMURA, Seigou and SUZUKI, Masamitsu and KOIKE, Akira and SUZUKI, Koichi and KAMIYA, Nobuhiko},
 month = {Dec},
 note = {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},
 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},
 year = {1984}
}