Can you do part c please Q3) A convergent-divergent nozzle has a cross-sectional area at the throat of 0.1 m².Air enters the nozzle at a stagnation pressure of 101 kPa and a stagnation femperatureof 15°C. The flow accelerates to sonic conditions at the throat and continues toaccelerate in the divergent section of the nozzle until a normal shock wave isgenerated at a cross-sectional area of 0.1775 m²a) Determine the Mach number immediately upstream of the normal shock wave.b) Calculate the static pressure and static temperature immediately upstream of thenormal shock wave.c) Determine the Mach number, static temperature and flow velocity immediatelydownstream of the normal shock wave.d) Calculatethe mass flow rate through the nozzle using only values immediatelyof the normal shock wave.downstream

fig: CD nozzle At=.1 m2A1=.1775m2P0=101 kPaT0=15oC=288 K A1=A2 A1A*=.1775.1=1.775 From isentropic…

Answered: Can you do part c please

Engineering

Mechanical Engineering

Can you do part c please

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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Question

Can you do part c please

Q3) A convergent-divergent nozzle has a cross-sectional area at the throat of 0.1 m².
Air enters the nozzle at a stagnation pressure of 101 kPa and a stagnation femperature
of 15°C. The flow accelerates to sonic conditions at the throat and continues to
accelerate in the divergent section of the nozzle until a normal shock wave is
generated at a cross-sectional area of 0.1775 m²
a) Determine the Mach number immediately upstream of the normal shock wave.
b) Calculate the static pressure and static temperature immediately upstream of the
normal shock wave.
c) Determine the Mach number, static temperature and flow velocity immediately
downstream of the normal shock wave.
d) Calculate
the mass flow rate through the nozzle using only values immediately
of the normal shock wave.
downstream

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