In a supersonic nozzle flow, the exit-to-throat area ratio is 10, p 0 = 10 atm. and

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In a supersonic nozzle flow, the exit-to-throat area ratio is 10, p ₀ = 10 atm. and the backpressure P _B = 0.04 atm. Calculate the angle 8 through which the low is deflected immediately after leaving the edge (or lip) of the nozzle exit.

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Thermodynamics An Interactive Approach

ISBN: 978-0130351173

1st edition

Authors: Subrata Bhattacharjee

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Posted Date: Apr 02, 2019 10:22 AM

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In a supersonic nozzle flow, the exit-to-throat area ratio is 10, p 0 = 10 atm. and

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00733 atm Also from Tabie AS v1 647 o Si... View the full answer

Thermodynamics An Interactive Approach

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