Let air at rest at the front edge of wing of an aeroplane and air passing over the surface of the wing at a fast speed `v`. If density of air is `rho`, then find out the higest value for `v` in stream line flow when atmospheric pressure is `P_(atm)`.

How does the speed v of sound in air depend on the atmospheric pressure P?

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.

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

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 ?

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

Air is streaming past a horizontal aeroplane wing such that the speed of air is 120 m/s over the upper surface and 90 m/s at the lower surface, with respect to the plane. If the density of air is 1.3kg/ m^(3) , find the difference in pressure between the top and bottom of the wing. If the wing is 10m long and has an average width of 2m, calculate the gross lift of the wing.