The flow speeds of air on the lower and upper surfaces of the wing of an aeroplane are v and 2 v respectively. The density of air is p and surface area of wing is A. The dynamic lift on the wing is

According to Bernoulli's theorem P1+12ρv12=P2+12ρv22  Given that v1=2v  and  v2=v P1+12ρ2v2=P2+12ρv2 ∴ P2−P1=ρv2/2 Now, force of dynamic lift = Pressure difference x surface area of wing =P2−P1×A =12ρv2A