Acknowledgments

Boundary layer control is a topic of constant concern in the area of aerodynamics. This study addresses a possible new method of affecting boundary layers and shock structure in supersonic flow. Nanosecond pulse dielectric barrier discharge plasma actuators are tested on a flat plate in a supersonic wind tunnel. Effects were observed using schlieren imaging to analyze changes in density gradients in the flow. While no noticeable results were found, the flow Mach numbers and electrical characteristics tested were very limited in variety due to complications with discharge formation and plate design. Much was learned to suggest improvements for further testing and this will facilitate later tests of similar technologies in this area of interest.