Maurice Tutor

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  • MCS,PHD
    Argosy University/ Phoniex University/
    Nov-2005 - Oct-2011

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  • Professor
    Phoniex University
    Oct-2001 - Nov-2016

Category > Management Posted 08 Jan 2018 My Price 5.00

convergent-divergent nozzle

1. Air is to flow through a convergent-divergent nozzle at 1.2 kg ·s−1 from a large reservoir in which the temperature is 20 ◦C. At the nozzle exit the pressure is to be 14 kPa and the Mach number 2.8. Assuming isentropic flow, determine the throat and exit areas of the nozzle, the pressures in the reservoir and the nozzle throat and the temperature and velocity of the air at exit.

2. A convergent-divergent nozzle originally designed to give an exit Mach number of 1.8 with air is used with argon (γ = 5/3). What is the ratio of the entry stagnation pressure to the exit pressure when a normal shock is formed just inside the nozzle exit?

Answers

Maurice Tutor
(5)
Status NEW Posted 08 Jan 2018 10:01 PM My Price 5.00

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