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Q.3 A converging-diverging nozzle is supplied by a huge air reservoir. The nozzle has a throat area of 10 cm2 and an exit area of 20 cm?. The reservoir conditions are Po = 300 kPa and T, = 30 °C. Determine the range of the back pressure over which (a) shocks appear in the nozzle, (b) oblique shocks form at the exit, and (c) expansion waves form. (d) Calculate the mass flow rate through the nozzle for the case in which a normal shock appears at the exit plane.

Q.3 A converging-diverging nozzle is supplied by a huge air reservoir. The nozzle has a throat area of 10 cm2 and an exit area of 20 cm?. The reservoir conditions are Po = 300 kPa and T, = 30 °C. Determine the range of the back pressure over which (a) shocks appear in the nozzle, (b) oblique shocks form at the exit, and (c) expansion waves form. (d) Calculate the mass flow rate through the nozzle for the case in which a normal shock appears at the exit plane.

Introduction to Chemical Engineering Thermodynamics
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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Q.3 A converging-diverging nozzle is supplied by a huge air reservoir. The nozzle has a throat area of 10 cm? and an exit area of 20 cm?. The reservoir conditions are P. = 300 kPa and To = 30 °C. Determine the range of the back pressure over which (a) shocks appear in the nozzle, (b) oblique shocks form at the exit, and (c) expansion waves form. (d) Calculate the mass flow rate through the nozzle for the case in which a normal shock appears at the exit plane.
Transcribed Image Text:Q.3 A converging-diverging nozzle is supplied by a huge air reservoir. The nozzle has a throat area of 10 cm? and an exit area of 20 cm?. The reservoir conditions are P. = 300 kPa and To = 30 °C. Determine the range of the back pressure over which (a) shocks appear in the nozzle, (b) oblique shocks form at the exit, and (c) expansion waves form. (d) Calculate the mass flow rate through the nozzle for the case in which a normal shock appears at the exit plane.
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