When an airfoil experiences a relatively quick change in angle of attack, a phenomenon called dynamic stall occurs. It consists of a leading edge vortex that grows and travels through the suction side of the airfoil. This impacts aerodynamic loads quite dramatically, especially when the vortex is shed. A brief summary of my work on this topic can be seen the in video below.

An even more in-depth analysis is my MsC thesis , in which I covered some more topics, like modal decomposition with POD (proper orthogonal decomposition) and SPOD (spectral proper orthogonal decomposition).