A compressed Air enters a convergent-divergent nozzle, at 4.0 atm, 300 K and at Mach 2.0. The nozzle is fitted at the exit of a 0.3 m constant diameter pipe and 2.0 m long that supplies the air. Assuming that the friction factor for the pipe is 0.003, and that a normal shock occurs in the pipe at Mach number 1.8, a) Find the length of the pipe between the location of the normal shock and the inlet of the nozzle. b) Claculate the throat and the exit plane diameters of the nozzle if the mach number at the exit plane is 2.0 c) Calculate the exit pressure. d) On a graph, skecth the variation of static and stagnation pressure along the pipe and the nozzle.
A compressed Air enters a convergent-divergent nozzle, at 4.0 atm, 300 K and at Mach 2.0. The nozzle is fitted at the exit of a 0.3 m constant diameter pipe and 2.0 m long that supplies the air. Assuming that the friction factor for the pipe is 0.003, and that a normal shock occurs in the pipe at Mach number 1.8, a) Find the length of the pipe between the location of the normal shock and the inlet of the nozzle. b) Claculate the throat and the exit plane diameters of the nozzle if the mach number at the exit plane is 2.0 c) Calculate the exit pressure. d) On a graph, skecth the variation of static and stagnation pressure along the pipe and the nozzle.
Elements Of Electromagnetics
7th Edition
ISBN:9780190698614
Author:Sadiku, Matthew N. O.
Publisher:Sadiku, Matthew N. O.
ChapterMA: Math Assessment
Section: Chapter Questions
Problem 1.1MA
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Transcribed Image Text:A compressed Air enters a convergent-divergent nozzle, at 4.0 atm, 300 K and at Mach 2.0. The
nozzle is fitted at the exit of a 0.3 m constant diameter pipe and 2.0 m long that supplies the air.
Assuming that the friction factor for the pipe is 0.003, and that a normal shock occurs in the pipe
at Mach number 1.8,
a) Find the length of the pipe between the location of the normal shock and the inlet of the nozzle.
b) Claculate the throat and the exit plane diameters of the nozzle if the mach number at the exit
plane is 2.0
c) Calculate the exit pressure.
d) On a graph, skecth the variation of static and stagnation pressure along the pipe and the nozzle.
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