As an airplane flies, the speed of air passing over the top of the wing is higher than the speed at which air flows below the wing. This creates a differential in the pressure above and below the wing. The weight of the airplane is supported by this pressure differential; this allows the aircraft to fly.
Here, the mass of the aircraft is 2*10^8 kg and the area of each wing is 1200 m^2. The speed at which air flows past the lower surface of the wing is 95 m/s. The density of air is 1.26 kg/m^3.
Using the Bernoulli equation, `P_l + (1/2)*rho*v_l^2 = P_u + (1/2)*rho*v_u^2`
`P_l - P_u = (1/2)*rho*(v_u^2 - v_l^2)`
To balance the weight of the aircraft, `P_l - P_u = (2*10^6)/2400`
`(2*10^6)/2400 = (1/2)*1.26*(v_u^2 - 95^2)`
=> `v_u^2 = 10347.75`
=> `v_u = 101.72`
The speed of air flowing above the wing is approximately 101.72 m/s