Experimental and Numerical Study of a Control Effect of Plasma Array on Flow Structure over Compression Ramp

摘要

The control effect of plasma array generated upstream of a 12-degree compression ramp was demonstrated in Mach-2 supersonic wind tunnel experiment. It was found that the shock wave position can be shifted upstream toward the Q-DC plasma array location that leads to a significant pressure redistribution over the ramp. A parametric study of plasma power and flow condition on pressure control was further performed by a numerical analysis based on two-dimensional Navier-Stokes equations with Baldwin-Lomax turbulent model. The change of pressure magnitude on the ramp surface was found to be an increasing function of plasma power in the tests and modelling both. A relative pressure decrease was also a linear increasing function of plasma power to flow enthalpy ratio that yields a task-related effectiveness. The control authority was also confirmed by CFD analysis, which also demonstrates an upper limit of the task-related effectiveness at higher plasma power.