Air flows through a converging-diverging nozzle with an area ratio of (2.9), (See Fig.2 nozzle exhausts into a constant-area insulated duct with a length of (50 cm) a meter of (1 cm). If the system back pressure is (50 kPa): P-50 kPa 1- Determine the range of reservoir pressures over which a normal shock wave will appear in the duct. Let (f = 0.002) in the duct. - If (75 %) of the duct length is removed and no normal shock wave will appear in the duct. The friction factor is remain unchanged. What is the Mach number at the exit of the

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Air flows through a converging-diverging nozzle with an area ratio of (2.9), (See Fig.2).
The nozzle exhausts into a constant-area insulated duct with a length of (50 cm) and
diameter of (1 cm). If the system back pressure is (50 kPa):
P-50 kPa
1- Determine the range of
reservoir pressures over
which a normal shock
wave will appear in the
duct. Let (f = 0.002) in
the duct.
2- If (75%) of the duct
length is removed and no
normal shock wave will appear in the duct. The friction factor is remain unchanged.
What is the Mach number at the exit of the
duct?
Transcribed Image Text:Air flows through a converging-diverging nozzle with an area ratio of (2.9), (See Fig.2). The nozzle exhausts into a constant-area insulated duct with a length of (50 cm) and diameter of (1 cm). If the system back pressure is (50 kPa): P-50 kPa 1- Determine the range of reservoir pressures over which a normal shock wave will appear in the duct. Let (f = 0.002) in the duct. 2- If (75%) of the duct length is removed and no normal shock wave will appear in the duct. The friction factor is remain unchanged. What is the Mach number at the exit of the duct?
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