Aerodrome (Kunyare)

Source of Aerodynamic Forces

• Pressure distribution on the surface

• Shear stress on the surface

• Both option 1 and 2

• None of the above

Altitude where temperature varies with respect to height.

• 0 - 10 km

• 0 - 11 km

• 0 - 12 km

• 0 - 13 km

Temperature from 11 km - 25 km

• 216.66 Kelvin

• 340 Rankine

• Varies with altitude

• None of the above

Consider a convergent duct with an inlet area 3 ft2 and an exit area 2.57 ft2. Air enters this duct with a velocity 700 ft/s and a density 0.002 slug/ft3 and air leaves with an exit velocity 1070 ft/s. Calculate the density of the air at the exit.

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Consider the incompressible flow of water through a divergent duct. The inlet velocity and area are 2 m/s and 1 m2 respectively, if the exit area is 3 times the inlet area, calculate the water flow velocity at the exit.

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A pipe is gradually tapering in size by 0.01 m2/m, what is the change in velocity per meter where the pipe is 0.4 m2 in cross section, if the velocity there is 30 m/s. Is the velocity increasing or decreasing?

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Consider an airfoil in a flow of air where far upstream of the airfoil, the pressure, velocity and density are 2116 lb/ft2, 100 mph, and 0.002377 slugs/ft3, respectively. At a given point A on the airfoil, the pressure is 2,070 lb/ft2. What is the velocity at point A?

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An airplane is flying at standard sea-level conditions. The temperature at a point on the wing is 250 K. What is the pressure at this point?

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Consider an airplane flying with the velocity of 60 m/s at a standard altitude of 3 km. at a point on the wing, the airflow velocity is 70 m/s. Calculate the pressure at this point. Assume incompressible flow.

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