Capt. A 380
I do not think it is so easy practically calculate CL with simple arithmetic. This is because every component of airplane (e.g fuselage) has effect on resultant aerodynamic force.
But just one contribution: L=W is incorrect,
The correct one is : L=W+Td,
What is Td?
I can describe it as the downward lift force created by Horizontal Stabilizer to equalize the moments about CG to zero. In another word, it is the downward force to create a counter moment to balance the moment created by wing.