The pressure on the top surface of an aeroplane wing is `0.8xx 10^5` Pa and the pressure on the bottom surface is `0.75 xx 10^5` Pa. If the area of each surface is `50 m^2`, the dynamic lift on the wing is

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

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

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 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 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) )