The speeds of air-flow on the upper and lower surfaces of a wing of an aeroplane are v₁ and v₂ , respectively. If A is the cross-sectional area of the wing and is the density of air, then the upward lift is

Step-by-step solution

According to Bernoulli's principle for streamline flow, the pressure P and velocity v at any two points on a streamline are related by P + 1 2 v^2 = constant . Let P₁ and P₂ be the pressures on the upper and lower surfaces of the wing respectively, with corresponding air speeds v₁ and v₂ . Applying Bernoulli's equation: P₁ + 1 2 v₁^2 = P₂ + 1 2 v₂^2 The pressure difference between the lower and upper surfaces is: P₂ - P₁ = 1 2 (v₁^2 - v₂^2) The upward lift force F is the product of the pressure difference and the c