Study of Transient and Unsteady Effects of Plasma Actuation in Transitional Flow over an SD7003 Airfoil

摘要

The short term transient and long term periodic unsteady effects of pulsed plasma actuation are studied using an unsteady, compressible Navier- Stokes solver for the case of a partially separated transitional flow over an SD7003 airfoil at 4 deg angle of attack and at Re=40,000. Forcing magnitude and its effect on the flow field is examined. Distinctly different behavior is observed parameters are adjusted. The unsteady simulations show that the actuators have a quick transient response, reattaching the separated flow within 2 non-dimensionalized units of time, but nearly independently of the forcing magnitude. Spikes in C(l), C(d), and C(m) are observed during reattachment, most likely due to vortex pairing at the trailing edge.