Shock-dominated flow control by plasma array: Pressure analysis including pressure-sensitive paint visualization

This work is focused on the experimental characterization of shock-dominated flow structures, parameters, and dynamics under control by a filamentary plasma array. Testing was performed in the supersonic blowdown test rig SBR-50 at the University of Notre Dame at flow Mach number M = 2 and stagnation pressure P0 = 1.7 bar. A shock wave (SW) generator composed of a symmetric 10 degrees wedge was installed on the top wall of a 710 mm long test section. The filamentary plasma array based on a Q-DC discharge was arranged on the opposite wall so that the main SW originating from the wedge impinged the plasma area. As a result of the SW-plasma interaction the flowfield was significantly modified over the test section, including an upstream shift of the main SW and pressure redistribution. Basic instrumentation included fast schlieren visualization, wall pressure measurements and Pitot-rake measurements at the end of the test section. Additionally, a fast Pressure Sensitive Paint (PSP) technique was employed to acquire details of the SW footprint and capture transitional effects after switching plasma off and on. Analysis of the data acquired by these complementary methods allowed for reconstruction of a three-dimensional portrait of shock-dominated flow interaction with the plasma zone. The mechanism of SWplasma interaction and the plasma effect on total pressure losses in the duct are also discussed.

Automated summary

This work focuses on experimental characterization of shock-dominated flow structures controlled by a filamentary plasma array. The study investigates the interaction between shock waves and plasma, effects on the flowfield, and the mechanism of plasma on total pressure losses in the duct.