Consider a venturi with a throat-to-inlet area ratio of 0.8, mounted on the side of an airplane fuselage. The airplane is in flight at standard sea level. If the static pressure at the throat is 2100 lb/ft2, calculate the velocity of the airplane. Note that standard sea level density and pressure are 1.23 kg/m3 (0.002377 slug/ft3) and 1.01 x 105 N/m2 (2116lb/ft3), respectively.

Velocity of the airplane = 154.703ft/s

Explanation:

Given

Pressure at the throat = Pt = 2100lb/ft²

Pressure at standard sea level = Ps = 2116lb/ft²

Throat-to-inlet area ratio = Tr= 0.8

Density at standard sea level = s = 0.002377 slug/ft³

First, we Calculate the velocity

Velocity, v = √(2(Ps - Pt)/(s(1/Tr)² - 1))

v = √((2 * (2116 - 2100)/(0.002377*1/0.8² - 1))

v = √((2 * 16)/(1.337 * 10^-3))

v = 154.703ft/s

the clapeyron equation (also called the clausius-clapeyron equation) relates the slope of a reaction line on a phase diagram to fundamental thermodynamic properties.

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