I'm trying to figure out what's the lift coefficient of an A320. What I'm doing is the following: during cruise, the lift is equal to the weight of the aircraft (mg) so that I used the cruise table taken from the FCOM to get the speed, the wing area is known (122.6 m^2) and I calculated using an
online tool the air density at FL290 (29000ft):
http://i.stack.imgur.com/l9g9N.png
The result is that the lift coefficient is 0.03029. Is it right for the assumptions given above? Next, if I want to relate the Cl with the Angle of Attack, what is the formula and the procedure? Thank you for your help.