590924.fig.001a
(a)
590924.fig.001b
(b)
590924.fig.001c
(c)
590924.fig.001d
(d)
Figure 1: (a) O-type computational domain of meshes for both the original and numerically tripped NACA 64-210 airfoils; (b) near mesh of the original airfoil; (c) near mesh of the airfoil tripped at 5% chordwise station; (d) close view of the tripped position on the 5% chordwise tripped airfoil.