Kakuda Branch Office, National Aerospace Laboratory(NAL)
出版者
航空宇宙技術研究所
出版者（英）
National Aerospace Laboratory(NAL)
雑誌名
航空宇宙技術研究所報告
雑誌名(英)
Technical Report of National Aerospace Laboratory TR-855
巻
855
ページ
13
発行年
1985-04
抄録（英）
The non-steady flow field of an impulsively started two dimensional nozzle was investigated, using double exposure interferometry. Two straight nozzles, one with a sharp-edged throat and the other with a rounded throat, were inserted into a 60mm × 150mm cross sectional shock tube. Incident shock Mach numbers were 2.0 and 2.4 in air. Continuous monitoring of wave interations, incident shock, secondary shock, Mach stem, and, slip line, were also carried out using a streak camera technique. Time-wise development of the density distribution of the whole flow field showed a datailed structure of the starting process and the wave interactions. The steady flow field upstream of secondary shock obtained by the experiment was compared with a numerical calculation using a finite difference method with a shock capturing procedure. Very good agreement between them was obtained. Double exposure holographic interferometry provides a useful tool for generating a gas dynamic data base for evaluation of numerical calculations.
二次元超音速ノズル内の非定常流れ場
naltr00855.pdf
(2.48MB)
