The present experimental work is motivated by the need for a fundamental understanding of the vortex-induced vibrations (VIV) of airfoils at high angles of attack from an aerodynamic perspective. The dynamic stall of a pitching NACA 643418 airfoil was investigated under reverse flow conditions, whereby the geometric trailing edge is located upstream of the geometric leading edge. The investigation focuses on the correlation between surface pressure, aerodynamic forces, and the evolution of the dynamic stall vortex (DSV) and the aerodynamic trailing edge vortex (TEV). A range of mean angles of attack from 5° to 25°, pitching amplitudes from 5° to 15°, and reduced frequencies between 0.05 and 0.21 were tested on an airfoil using a combination of particle image velocimetry (PIV) and surface pressure measurements.