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25 June, 20:33

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.

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  1. 25 June, 23:02
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    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
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