The flow structure and turbulent characteristics of an airfoil at various Reynolds numbers (Re_c = 1.5×10^4,
2.0×10^4, 2.5×10^4) have been investigated considering two angles of attack (α = 10^o and α = 12^o). PIV
measurements have been performed and time-averaged and instantaneous results were presented utilizing
vorticity, profiles of streamwise velocity, Reynolds shear stress, and turbulent kinetic energy
distributions. The results have shown that both the Rec and α significantly affect the flow characteristics
around the airfoil. Furthermore, the change in flow characteristics between the stall and post-stall angles
was elaborated and compared with each other, as being in good agreement with the available literature.
The turbulent fluctuations in the airfoil wake, as well as in the suction side, were obtained to be more
intense at post-stall angle compared with the stall condition. Besides, due to the earlier flow separation,
post-stall condition presented a larger wake and the shedding of vortices formed by the leading and
trailing edges of the airfoil.