The lift force acting on the wing of an aeroplane is `3000 N`. If the area of the wing is `10m^(2)` and velocity of air on the lower surface of the wing is `40m`/`s`. Velocity of air on the upper surface of the wing is (density of air is `2kg`/`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) .

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) )

The velocity of sound in air at 27^(@)C is 330 m/s. the velocity of sound when the temperature of the gas is raised to 227^(@)C is

The speed of the wind passing over the wings of a small aeroplane is 70 m/s and below the wing is 60 m/s. If the mass of the plane is 1000 kg and the area of wing is 14 m^(2), then what will be ther net vertical force on the aeroplane ? ? (Density of air =1.2 kg//m^(3) and g=10 m//s^(2))

Calculate the r.m.s velocity of air molecules at S.T.P. Density of air at S.T.P. is 1.29 kg m^(-3)

The speed of flow past the lower surface of a wing of an aeroplane is 50ms^(-1) . What speed of flow over the upper surface will give a dynamic lift of 1000 pa ? Density of air =1.3 kgm^(-3)

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) )

A plane is in level flight at constant speed and each of its wings has an area of 25m^(2) . If the speed of the air is 180km//h over the upper wing surface, determine the plane's mass . (Take air density to be 1 kg//m^(3) ). g=9.8m//s^(2) .

An aeroplane of mass 3xx10^(4)kg and total wing area of 120 m^(2) is in a level flight at some height the difference in pressure between the upper and lower surfaces of its wings in kilo pascal is (g=10m//s^(2))

Air is streaming past a horizontal airplane wing such that its speed is 90 ms^(-1) at the lower surface and 120 ms^(-1) over the upper surface. if the wing is 10 m long and has an average width of 2 m , the difference of pressure on the two sides and the gross lift on the wing respectively, are (density of air =1.3kgm^(-3) )