An aircraft is moving on a runway for its take off. The wind speed on the lower and upper surface of the wings are 'v' and `'sqrt2'v`. If the density of air is `rho` and surface area of the wing is A, the upward force exerted on thei wings will be

In a test experiement on a model aeroplane in a wind tunnel, the flow speeds on the lower and upper surfaces of the wing are upsilon and upsilonsqrt(2) respectively. If the density of air is rho and the surface area of the wings is A, what is the dynamic lift on the wing of aeroplane.

The flow speeds of air on the lower and upper surfaces of the wing ofan aeroplane are v and sqrt2v respectively. A is the area of the wing and rho is the density of th e surrounding air. What is the force of the dynamic lift on the wing ?

In a wind tunnel experiment the pressure on the upper and lower surfaces of the wings are 0.90xx10^(5)Pa and 0.91 xx 10^(5)Pa respectively. If the area of the wing is 40 m^(2) the net lifting force on the wing is

Air is blowing across the horizontal wings of an aeroplane in such a way that its speeds below and above the wings are 80 m/s and 120 m/s respectively. If the density of air is 1.2 kg/m^3 then the pressure difference between the lower and the upper sides of the wings will be

In a wind tunnel experiment the pressure on the upper and lower surfaces of the wings are 0.90 xx 10^(5) Pa and 0.91 xx10^(5) Pa respectively .If the area of the wings is 40 m^(2) the net liftng forcw on the wing is

In a wind tunnel experiment the pressure on the upper and lower surfaces of the wings are 0.90 xx 10^(5) Pa and 0.91 xx10^(5) Pa respectively .If the area of the wings is 40 m^(2) the net liftng forcw on the wing is

A fully loaded Boeing aircraft has a mass of 3.3xx10^(5) kg . Its total wing area is 500 m^(2) . It is in level flight with a speed of 960 km//h . (a) Estimate the pressure difference between the lower and upper surfaces of the wings (b) Estimate the fracitional increases in the speed of the air on the upper surfaces of the wing relative to the lower surface. The density of air is 1.2 kg//m^(3) .

A fully loaded Boeing aircraft has a mass of 3.3xx10^(5) kg . Its total wing area is 500 m^(2) . It is in level flight with a speed of 960 km//h . (a) Estimate the pressure difference between the lower and upper surfaces of the wings (b) Estimate the fractional increases in the speed of the air on the upper surfaces of the wing relative to the lower surface. The density of air is 1.2 kg//m^(3) .