What are the typical lift, lift coefficient and drag coefficient for a A320 in cruise?
In s/l flight, weight and lift are practically equal, so  –if those are metric tons– the lift will be 72000 x 9,8 = 705600 N. Now, concerning the CL, we may solve for CL the expression for lift:

$C_L = \frac{2 · L}{\rho V^2  S } $

$C_L = \frac{2\cdot9.8\cdot72000} { 0.366 · 230^2 · 122.6 }$

$C_L = 0.595$

Now, assuming a L/D of 15, the CD = 0,594/15 = 0,039