热科学学报（英文版）2005，Vol.14Issue(3)：258-263,271,7.
Transonic Instability in Entrance Part of Mixing Chamber of High-Speed Ejector
Transonic Instability in Entrance Part of Mixing Chamber of High-Speed Ejector
摘要
Abstract
The paper deals with experimental and numerical study of flow structure in two-dimensional model of supersonic ejector. Schlieren pictures of flow structure were taken, static pressure distributions on side wall were measured and ture were taken, static pressure distributions on side wall were measured and Fluent software to calculate the flow structure in supersonic ejector was used. For certain region of back pressure he terminal shock wave is close to the trailing edge of the primary flow nozzle and a transonic instability occurs. The instability causes the movement of position of boundary layer separation,the structure of shock waves changes and all flow structure oscillates. The movie of these regimes during schlieren experiments was taken and relevant numerical modelling was performed.关键词
transonic instability/ejector/shock wavesKey words
transonic instability/ejector/shock waves分类
数理科学引用本文复制引用
Vaclav Dvorak,Pavel Safarik..Transonic Instability in Entrance Part of Mixing Chamber of High-Speed Ejector[J].热科学学报（英文版）,2005,14(3):258-263,271,7.基金项目
This project was realized by financial support from the state resources by Czech Science Foundation, grant no. 101/05/P298 "Optimization and control of mixing processes"and by financial support from MSM 4674788501. （）
