Separated flow response to single pulse actuation

The response of a separated flow over a two-dimensional wing to a short duration disturbance from a Lorentz force leading-edge actuator is presented. The transient flow structures and lift force measurements were obtained from PIV measurements. The dependence of the lift response on actuator pulse duration, pulse amplitude, and direction of actuation was documented. The flow structures in the separated shear layer were identified using Finite Time Lyapunov Exponent (FTLE) method. The direction of the actuator pulse had a significant effect on the initial development of the shear layer, but the larger scale envelope of the separated flow had essentially the same response, irrespective of the direction of actuation.