Air flows from a tank through a converging-diverging nozzle. A normal shock wave stands at a section in the nozzle where the area is A = 13 cm². The area of the throat is A = 9 cm². Based on 1D compressible duct flow: a. Sketch the pressure distribution p/p,for the nozzle. Is the nozzle choked? b. Calculate the Mach numbers on both sides of the normal shock wave. c. Calculate the pressure ratio p2/p1 across the shock wave.
Air flows from a tank through a converging-diverging nozzle. A normal shock wave stands at a section in the nozzle where the area is A = 13 cm². The area of the throat is A = 9 cm². Based on 1D compressible duct flow: a. Sketch the pressure distribution p/p,for the nozzle. Is the nozzle choked? b. Calculate the Mach numbers on both sides of the normal shock wave. c. Calculate the pressure ratio p2/p1 across the shock wave.
Introduction to Chemical Engineering Thermodynamics
8th Edition
ISBN:9781259696527
Author:J.M. Smith Termodinamica en ingenieria quimica, Hendrick C Van Ness, Michael Abbott, Mark Swihart
Publisher:J.M. Smith Termodinamica en ingenieria quimica, Hendrick C Van Ness, Michael Abbott, Mark Swihart
Chapter1: Introduction
Section: Chapter Questions
Problem 1.1P
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Transcribed Image Text:Air flows from a tank through a converging-diverging nozzle. A normal
shock wave stands at a section in the nozzle where the area is A = 13 cm². The area
of the throat is A = 9 cm². Based on 1D compressible duct flow:
a. Sketch the pressure distribution p/p,for the nozzle. Is the nozzle choked?
b. Calculate the Mach numbers on both sides of the normal shock wave.
c. Calculate the pressure ratio P2/P1 across the shock wave.
d. How does the critical area change across the shock wave? Why?
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