{[ promptMessage ]}

Bookmark it

{[ promptMessage ]}

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

This preview shows pages 1–3. Sign up to view the full content.

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 force developed by the rocket must be determined. 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

This preview has intentionally blurred sections. Sign up to view the full version.

View Full Document
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 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
This is the end of the preview. Sign up to access the rest of the document.

{[ snackBarMessage ]}

### Page1 / 3

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

This preview shows document pages 1 - 3. Sign up to view the full document.

View Full Document
Ask a homework question - tutors are online