cvprobs - EGN 3353C - Fluid Mechanics Spring Semester 2011...

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EGN 3353C - Fluid Mechanics Spring Semester 2011 Supplementary Handout: Control-Volume Problems 1. A rocket is to be mounted horizontally on a test stand. To design the test stand, the thrust u e Assume that the flow quantities at the exit plane of the nozzle are known. Note that the flow exits the nozzle at supersonic speeds. (a) Determine an expression for the thrust force developed by the rocket. (b) Compute the thrust given that the diameter of the nozzle exit is d e = 3 . 8 m, the mass flow is ˙ m = 4200 kg / s, the velocity at the nozzle exit is u e = 3200 m / s, the static pressure at the nozzle exit is p e = 6 · 10 4 Pa, and the atmospheric pressure is p = 1 . 0 · 10 5 Pa. 1
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2. A low-speed wind tunnel is used to measure the drag force acting on a wing. Measurements indicate that some distance downstream of the wing, the wake leads to a reduction in the velocity profile as shown below. x y u ( y ) u 1 Upstream of the wing, the velocity is measured to be u . Assume that the wing is rectangular, i.e., the cross-section does not vary over its span
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This note was uploaded on 09/05/2011 for the course EGN 3353C taught by Professor Lear during the Spring '07 term at University of Florida.

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cvprobs - EGN 3353C - Fluid Mechanics Spring Semester 2011...

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