Abstract
Results are presented from the experimental study of the spatial structure and spectrum of the nanosecond distributed sliding surface discharge (plasma sheet) in quiescent air and in a supersonic and transonic gas flow behind a plane shock wave. Discharge investigations were carried out in air flow with velocities up to 1600 m/s within density range of 0.08-0.40 kg/m3. Different structures of plasma glow were observed for the laminar and turbulent flow regimes in the boundary layer. Analysis of the obtained images clearly shows that character of the glow of the discharge changes with change of the boundary layer structure. The analysis of the experimental data shows that the radiation spectrum of sliding surface discharge changes in gas flow after a shock wave
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
