###### Fluid Mechanics: Fundamentals and Applications

162 SOLVED PROBLEMS

Question: 5.10

## Bernoulli Equation for Compressible Flow Derive the Bernoulli equation when the compressibility effects are not negligible for an ideal gas undergoing (a) an isothermal process and (b) an isentropic process. ...

The Bernoulli equation for compressible flow is to...
Question: 14.11

## Design of a New Geometrically Similar Pump After graduation, you go to work for a pump manufacturing company. One of your company’s best-selling products is a water pump, which we shall call pump A. Its impeller diameter is DA = 6.0 cm, and its performance data when operating at nA = 1725 rpm ...

(a) For a given table of pump performance data for...
Question: 14.2

## Selection of Pump Impeller Size A washing operation at a power plant requires 370 gallons per minute (gpm) of water. The required net head is about 24 ft at this flow rate. A newly hired engineer looks through some catalogs and decides to purchase the 8.25-in impeller option of the Taco Model 4013 ...

For a given flow rate and net head, we are to calc...
Question: 12.17

## Exit Conditions of Fanno Flow in a Duct Air enters a 27-m-long 5-cm-diameter adiabatic duct at V1 = 85 m/s, T1 = 450 K, and P1 = 220 kPa (Fig. 12–67). The average friction factor for the duct is estimated to be 0.023. Determine the Mach number at the duct exit and the mass flow rate of air. ...

Air enters a constant-area adiabatic duct of given...
Question: 12.16

## Choked Fanno Flow in a Duct Air enters a 3-cm-diameter smooth adiabatic duct at Ma1 = 0.4, T1 = 300 K, and P1 = 150 kPa (Fig. 12–66). If the Mach number at the duct exit is 1, determine the duct length and temperature, pressure, and velocity at the duct exit. Also determine the percentage of ...

Air enters a constant-area adiabatic duct at a spe...
Question: 12.15

## Rayleigh Flow in a Tubular Combustor A combustion chamber consists of tubular combustors of 15-cm diameter. Compressed air enters the tubes at 550 K, 480 kPa, and 80 m/s (Fig. 12–58). Fuel with a heating value of 42,000 kJ/kg is injected into the air and is burned with an air–fuel mass ratio of 40. ...

Fuel is burned in a tubular combustion chamber wit...
Question: 12.9

## Shock Wave in a Converging–Diverging Nozzle If the air flowing through the converging–diverging nozzle of Example 12–7 experiences a normal shock wave at the nozzle exit plane (Fig. 12–35), determine the following after the shock: (a) the stagnation pressure, static pressure, static temperature, ...

Air flowing through a converging–diverging nozzle ...
Question: 12.7

## Airflow through a Converging–Diverging Nozzle Air enters a converging–diverging nozzle, shown in Fig. 12–28, at 1.0 MPa and 800 K with a negligible velocity. The flow is steady, one-dimensional, and isentropic with k = 1.4. For an exit Mach number of Ma = 2 and a throat area of 20 cm², determine ...

Air flows through a converging–diverging nozzle. T...
Question: 12.6