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## 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.

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.