A Study of the Flow in a Simulated Supersonic Electrofluiddynamic Generator Flow Channel.
AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING
Pagination or Media Count:
Schlieren photographs together with static pressure measurements were used to observe the flow field generated in a simulated two-dimensional electrofluiddynamic generator flow channel. The flow channel was designed to obtain nominal Mach 2.6 flow conditions at the probe tip. It was shown that the extent of the expansion process at the probe tip could be increased as much as sixty per cent by impinging a secondary shock on the shear layer downstream of the probe tip separation edge. It was observed that the closer the shock impinged to the probe tip separation edge, the stronger the expansion process. Author
- Electric Power Production and Distribution
- Plasma Physics and Magnetohydrodynamics