A Study of the Flow in a Simulated Supersonic Electrofluiddynamic Generator Flow Channel.
Abstract
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)
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1969
- Accession Number
- AD0851945
Entities
People
- Edwin W. Brenner
Organizations
- Air Force Institute of Technology