Question: How do I calculate the lift for a certain surface area?
Here is the formula needed to calculate the lift force on a wing.
L = (1/2)*C*ρV^2*A
where
L = lift (Newtons)
C = Lift coefficient (dimensionless)
ρ = air density (kg / m^3)
V = velocity (m/s) (of air over wing)
A = area of wing (m^2)