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 temperature 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

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 temperature 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

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

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
downstream of the normal shock wave.

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