FLUID MECHANICS FRANK WHITE 4TH EDITION SOLUTION MANUAL PDF

Solution: The student should perhaps verify that Qp has units of power, so that is a dimensionless ratio. What is the only possible dimensionally homogeneous relation for this flow rate? Write this in dimensional. The relation is now.

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The adiabatic steady-flow energy equation 9. Use two approaches: a an ideal gas from Table A. Solution: For steam, take. Solution: For oxygen, take. How fast can a two-dimensional cylinder travel in sea-level standard air before compressibility becomes important somewhere in its vicinity?

Thus 8. Estimate the exit velocity and temperature. Solution: At saturation conditions, steam is At C and 1. This exit flow is supersonic , with a Mach number exceeding 2. We are assu ming with this calculation that a supersonic shock wave does not form. Solution: From Table A. Convert C to K. Compute a p2 , b the heat added between sections, c the entropy change between sections, and d the mass flow per unit area.

Hint: This problem requires the continuity equation. Using a control-volume analysis from Eq. The 3. If the exhaust gas has nozzle exit diameter is 45 cm, and the jet exit density is 0.

Solution: a From Eq. Determine its Mach number. Smith and A. Lawson, J. Solution: We may compute these values by differentiating Eq.

Solution: At m, from Table A. From the data of Prob. Show that the energy Eq. Sketch this ellipse; label the intercepts and the regions of subsonic, sonic, and supersonic flow; and determine the ratio of the major and minor axes. Solution: In Eq. Estimate a the density change; b the temperature change; and c the velocity change across the wave. Solution: For air at Discuss the type of reflected pulse which occurs, and the boundary conditions which must be satisfied, when the wave strikes normal to, and is reflected from, a a solid wall; and b a free liquid surface.

Using Prob. Solution: It probably makes little difference, but estimate at m, p. After determining the altitude of Indianapolis, find the Mach number of these cars and estimate whether compressibility might affect their aerodynamics. Estimate the temperature in C at the front stagnation point.

At what Mach number would it have a front stagnation point temperature of C? Solution: At km standard altitude, T. For a air and b helium, compute the maximum pressure and the maximum velocity attainable by expansion or compression.

The results follow in sequence: kk-- 1. Then o. Assuming isentropic flow, if the rocket thrust is 2 MN, estimate a the exit velocity; and b the mass flow of hydrogen. Solution: Compute c. From Prob. At what Mach number will the error be 4 percent?

Solution: Estimate the air specific weight in the manometer to be, say, 0. What would be a source of error if a shock wave were formed in front of the probe?

If there is a shock wave formed in front of the probe, this formula will yield the air velocity inside the shock wave, because the probe measures p inside the shock. The o2 stagnation pressure in the outer stream is greater, as is the velocity outside the shock. Let us help by giving the density-ratio formula:. Estimate a the mass flow rate; and b the Mach number at the throat.

We can then solve for exit temperature, density, and velocity, finally mass flow: kg TR. Using the Steam Tables, estimate a the temperature; b the velocity; and c the mass flow at this section.

Is the flow subsonic? Using k 1. That was quick. Instead, plow about in the S. Steam Tables, assuming constant entropy: At T.

Estimate, at this section, a V; b Ma; and c o. Solution: For oxygen, from Table A. Assuming isentropic flow, compute the pressure a in the tank and b in the atmosphere. Then the exit jet temperature is. Is the flow choked? Solution: Use the energy equation to calculate T. A1 Compute the initial mass flow rate a for an ideal gas; and b from the Steam Tables.

Solution: For steam, from Table A. The nozzle is choked and exits at a pressure higher than 1 atm. Use Eq.

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Fluid Mechanics Cengel solutions manual Chap Jump to Page. Search inside document. Chapter 9 Compressible Flow 9. Steam is nearly ideal in this range. From Eq. This ellipse is shown below. The axis ratio is Ans. Then Ans Ans 0. This is less than 0. Solution: At km standard altitude, T Then kK. Then 1. Then o p 1. Then the exit jet temperature is Fig. Ans 94 s kg Ans A1 Then the critical 1.

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