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Q.4 A converging-diverging nozzle, which is shown in the figure, is supplied with air from a large tank where the pressure is P, and exhausts to the atmosphere with a pressure of Ph. The area A at distance x from the throat is given by (A=A, (1+0.75x/L), where A, is the throat cross-sectional area and L is the total length of the diverging part of the nozzle. At a certain pressure ratio P/Pp, a normal shock wave stands in the nozzle at a point where the Mach number before the shock is 1.7. Find the position of the normal shock wave from the throat, and the pressure ratio P/Po.

Q.4 A converging-diverging nozzle, which is shown in the figure, is supplied with air from a large tank where the pressure is P, and exhausts to the atmosphere with a pressure of Ph. The area A at distance x from the throat is given by (A=A, (1+0.75x/L), where A, is the throat cross-sectional area and L is the total length of the diverging part of the nozzle. At a certain pressure ratio P/Pp, a normal shock wave stands in the nozzle at a point where the Mach number before the shock is 1.7. Find the position of the normal shock wave from the throat, and the pressure ratio P/Po.

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.4 A converging-diverging nozzle, which is shown in the figure, is supplied with air from a large tank where the pressure is P, and exhausts to the atmosphere with a pressure of P. The area A at distance x from the throat is given by (A=A, (1+0.75x/L), where A, is the throat cross-sectional area and L is the total length of the diverging part of the nozzle. At a certain pressure ratio P/Pb, a normal shock wave stands in the nozzle at a point where the Mach number before the shock is 1.7. Find the position of the normal shock wave from the throat, and the pressure ratio РУР. Po Ps L
Transcribed Image Text:Q.4 A converging-diverging nozzle, which is shown in the figure, is supplied with air from a large tank where the pressure is P, and exhausts to the atmosphere with a pressure of P. The area A at distance x from the throat is given by (A=A, (1+0.75x/L), where A, is the throat cross-sectional area and L is the total length of the diverging part of the nozzle. At a certain pressure ratio P/Pb, a normal shock wave stands in the nozzle at a point where the Mach number before the shock is 1.7. Find the position of the normal shock wave from the throat, and the pressure ratio РУР. Po Ps L
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