The current research is based on a flow structure interaction problem in which a Micro Air Vehicle (MAV) wing experiences flow induced vibrations. The goal is to use low dimensional tools to create closed feedback flow control methods for Micro Air Vehicles. The combined Proper Orthogonal Decomposition (POD) and Linear Stochastic Estimation (LSE) techniques utilize the dynamic strain encountered by the wing, to estimate the velocity flow field. When combined with piezoelectric devices, these techniques aid in the development of a MAV wing that has both sensing and morphing capabilities. In this paper we review the work to date where we have demonstrated the ability to estimate the wake flow velocity from dynamic strain. We then compare the strain spectrum from the MAV wing between measurements made both with and without piezoelectric actuation and find that we are able to change the strain spectrum in such a way to suggest that we can obtain significant control authority with the current setup.