Fox And Mcdonald's Introduction To Fluid Mechanics
9th Edition
ISBN: 9781118921876
Author: Pritchard, Philip J.; Leylegian, John C.; Bhaskaran, Rajesh
Publisher: WILEY
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Textbook Question
Chapter 12, Problem 67P
The exit section of a convergent-divergent nozzle is to be used for the test section of a supersonic wind tunnel. If the absolute pressure in the test section is to be 140 kPa, what pressure is required in the reservoir to produce a Mach number of 5 in the test section? For the air temperature to be −20°C in the test section, what temperature is required in the reservoir? What ratio of throat area to test section area is required to meet these conditions?
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An ideal isentropic nozzle is attached to an infinite reservoir that has stagnation conditions 3 MPa and 2250 K, and a constant specific heat of 1.2. If the nozzle's static exit pressure is 38.871 kPa, what is the exit static temperature? Also determine the nozzle's exit Mach number, stagnation pressure, and stagnation temperature.
(a) Write Area-Velocity relation for compressible flows through a supersonic Convergent-Divergent nozzle
What is the importance of it?
(b) Write Area-density relation for compressible flows through a supersonic Convergent-Divergent nozzle
What is the importance of it?
(c) Write Area-Mach relation for compressible flows through a supersonic Convergent-Divergent nozzle
What is the importance of it?
(d) Plot the variation of density, pressure, temperature, velocity and Mach number for compressible flows
through a supersonic Convergent-Divergent nozzle
Note: Do NOT derive above relations.
The velocity ratio (v1/v2) of an isentropic flow through a supersonic wind tunnel is 0.615. if the mach number at the tunnels entry section is 0.95 find the value of mach number at the exit
Chapter 12 Solutions
Fox And Mcdonald's Introduction To Fluid Mechanics
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