Data underlying the publication: An experimental study of the unsteady aerodynamics of a static DU91-W2-150 airfoil at large angles of attack

The main goal of this research is to experimentally investigate the unsteady aerodynamics of a static airfoil at large angles of attack (AoA), with a focus on the wake flow dynamics, vortex shedding characteristics and airfoil loading. This dataset contains the experimental measurement of a static DU91-W2-150 airfoil in a closed wind tunnel. This experimental study tested the airfoil under a wide range of AoA from 0◦ to 310◦ at three Reynolds numbers (Re) from 2×10^5 to 8×10^5. Pressure on the airfoil surface was measured and Particle Image Velocimetry (PIV) measurements were conducted to capture the flow field in the wake.