<Dl> <Dd> C L = 2 π (A 0 + A 1 / 2) (\ displaystyle \ C_ (L) = 2 \ pi (A_ (0) + A_ (1) / 2)) </Dd> </Dl> <Dd> C L = 2 π (A 0 + A 1 / 2) (\ displaystyle \ C_ (L) = 2 \ pi (A_ (0) + A_ (1) / 2)) </Dd> <P> The moment M about the leading edge depends only on A 0, A 1 (\ displaystyle A_ (0), A_ (1)) and A 2 (\ displaystyle A_ (2)), as </P> <Dl> <Dd> C M = − 0.5 π (A 0 + A 1 − A 2 / 2) (\ displaystyle \ C_ (M) = - 0.5 \ pi (A_ (0) + A_ (1) - A_ (2) / 2)) </Dd> </Dl>

Where is the greatest amount of lift generated on an aerofoil