Question

1. A converging-diverging
nozzle is designed assuming steady isentropic flow. Air enters the
nozzle at 427°C and 1000 kPa with negligible velocity. The exit
Mach number is 2 and throat area is 20 cm^{2}.
Determine:

a. The throat velocity

b. The mass flow rate

c. The exit area

2. The nozzle now has an exit
area of 4 cm^{2}. Air enters the nozzle with a total
pressure of 1200 kPa, and a total temperature of 127^{o}C.
Determine the mass flow rate for back pressure of :

d. 900 kPa

e. 634 kPa

f. 400 kPa

Answer #1

1. A converging-diverging
nozzle is designed assuming steady isentropic flow. Air enters the
nozzle at 427°C and 1000 kPa with negligible velocity. The exit
Mach number is 2 and throat area is 20 cm2.
Determine:
a. The throat velocity
b. The mass flow rate
c. The exit area
2. The nozzle now has an exit
area of 4 cm2. Air enters the nozzle with a total
pressure of 1200 kPa, and a total temperature of 127oC.
Determine the mass flow rate for back pressure of...

1. Air enters a converging-diverging
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(iii) Calculate the...

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Assume that air is drawn steadily through a frictionless,
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A turboprop engine consists of a diffuser, compressor,
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1. In a typical nozzle, air is used as a medium to undergo
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The mass flow rate is 2.5 [kg/s]. Assume the nozzle is well
insulated.
Determine the exit temperature of the steam.

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