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Lift=Cl*(r*V^2)/2*A

Cl=2*pi*AoA

Drag=Cd*(r*V^2)/2*A

Cd=Cd0+Cl^2/(pi*A*R*e)

Now I have two questions. First, are these the correct formulas for finding lift and drag on an airplane? Second, what are all of the variables? I think I know some of them, but I would like to be sure so please include them.