Air stream flows horizontally past an aeroplane wing of surface area `4 m^(2)`. The speed of air over the top surface is `60 ms^(-1)` and under the bottom surface is `40 ms^(-1)` The force of lift on the wing is (density of air =`1 kgm^(-3)`)

Air streams horizontally past an air plane. The speed over the top surface is 60 m/s, and that under the bottom surface is 45 m/s. The density of air is 1.293 kg/ m^(3) , then the difference in pressure

Air streams horizontally past an air plane. The speed over the top surface is 60 m/s, and that under the bottom surface is 45 m/s. The density of air is 1.293 kg/ m^(3) , then the difference in pressure

The velocity of the wind over the surface of the wing of an aeroplane is 80ms^(-1) and under the wing 60ms^(-1) . If the area of the wing is 4m^(2) , the dynamic lift experienced by the wing is [density of air =1.3kg.m^(-3) ]

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.

A plane is in level flight at constant speed and each of its two wings has an area of 25 m^(2) . If the speed of the air on the upper and lower surfaces of the wing are 270 km h^(-1) and '234 km h^(-1)' respectively, then the mass of the plane is (Take the density of the air =1 kg m^(-3) )