anticipated. With increasing Reynolds Num- 
ber, it may be expected that the section maxi- 
mum lift coefficient will increase (from the 
higher energy turbulent boundary layer) and 
that the section drag coefficient will decrease 
(similar to that of the smooth plate). These 
effects are illustrated by the graphs of figure 
1.27. 
The characteristics depicted in figure 1.27 
are for the NACA 4412 airfoil (4 percent 
59