In a test experiment on model airplane in a wind tunnel, the flow of air speed on the upper and lower surfaces of the wing are 70m`s^(-1)` and 63m`s^(-1)` respectively. What will be lift on wing of area 4`m^(2)` ? (`rho_(air )`=1.3`kgm^(-3)`)

In a test experiment on a model aeroplane in a wind tunnel, the flow speeds on the upper and lower surfaces of the wing are 70ms^(-1) and 83ms^(-1) respectively. What is the lift on the wing, if its area is 2.5m^(2) ? Take the density of air to be 1.3kgm^(-3)

In a test experiment on a model aeroplane in a wind tunnel, the flow speeds on the upper and lower surfaces of the wing are 70 ms^(-1) and 63 ms^(-1) respectively. What is the lift on the wing if its area is 2.5 m^(2) ? Take the density of air to be 1.3 kg m^(-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) )

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 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)

The wavelength of the sound emitted by a tuning fork in air is 3m. Speeds of sound in air and in water are 330 m/s and 1400 m/s respectively. Wavelength of this sound in water 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))

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) .

Calculate the minimum distance in air required between the source of sound and the obstacle to hear an echo. Take speed of sound in air = 350 m s^(-1)

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) )