Determining the coefficient of lift

Main Question or Discussion Point

Been working on a new way of determining the lift coefficient besides the thin airfoil theory,and I don't know if there is already such a method or if i'm wrong.Plz Help.We know,
L=CL×1/2ρv^2A
Now,as lift is a force,then it should be as L=mμ, where μ is the "upwards acceleration".
So, L=mμ=CL×1/2ρv^2A
⇒mμ=CL×1/2ρ[(0)^2+2as]A, because v^2=u^2+2as,and here the initial velocity will be zero.
⇒mμ=CL×1/2ρ2asA
⇒mμ=CL×ρ×a×s×A
⇒CL=mμ/ρasA
That's it.Am I wrong somewhere?......plz reply.

I suppose the algebra seems correct, but I am not really certain that this would ever be useful. For level flight, there isn't going to be any acceleration upward or downward since $ma = \Sigma F$ and $\Sigma F$ will be zero, yet there is certainly still lift. In other words, your $\mu$ is likely going to be meaningful. Further, for level flight at constant airspeed, your $a$ term will also be zero, meaning your whole $C_L$ will have a $0/0$ term in it and will be undefined, yet $C_L$ is certainly defined and nonzero at that point.