Anya Jones is an Associate Professor in the Department of Aerospace Engineering at the University of Maryland, College Park, USA. She received her PhD in experimental aerodynamics from the University of Cambridge, United Kingdom, her S.M. in aeronautics and astronautics from MIT, and her B.S. in aeronautical and mechanical engineering from Rensselaer Polytechnic Institute. Her research is focused on the experimental fluid dynamics of unsteady and separated flows. Her current projects focus on wing performance in large-amplitude gust encounters, separated and reverse flow rotor aerodynamics, and flight through airwakes and other unsteady environments. Prof. Jones has been awarded the AFOSR Young Investigator Award (2012), NSF CAREER Award (2016), and the PECASE from the White House (2016). In 2017 she was awarded a Fulbright Scholar Award to the Technion in Haifa, Israel (2017-2018) and an Alexander von Humboldt Research Fellowship to TU Braunschweig in Germany (2018). She is currently chair of a NATO Research Technology Organization task group on gust response and unsteady aerodynamics, an associate fellow of AIAA, and a member of the Alfred Gessow Rotorcraft Center. ‘ Dr. Jones’ presentation will focus on MAV behavior in turbulent conditions and the ability to predict unsteady flows and mitigate their effects. One of the challenges of MAV flight is controlled flight through the unsteady environments that exist in urban areas, in airwakes, and in extreme weather. These highly unsteady flows often result in large force transients due to flow separation and the formation of large-scale vortices. The growth and motion of these vortices can have a large impact on the resulting force transient and recovery, necessitating advanced control either locally via flow control or more globally at the vehicle level. The current work focuses on wind gusts and wing maneuvers that result in changes to the relative flow that are of the same order of magnitude as the freestream flow. In these cases, flow separation is significant, so the classical linear solution for the flow does not apply and aggressive control is required. Separated shear layers emanating from the wing tend to roll up into leading and trailing edge vortices that are shed into the wake. The formation and motion of these vortices are characterized via a series of canonical experiments in an attempt to better understand their contribution to aerodynamic forcing and their relative importance as compared to other sources of airloads (e.g., added mass and virtual camber). The results are then used to construct a physics-based low order model of highly separated flows, and thus explore the possibility of predicting unsteady and transient loading, as well as gain insight as to where flow control might be used most effectively to mitigate force transients and/or hasten flow recovery.