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The gas in a rocket combustion chamber is at 120 psia and 1600°R (Fig. 2.14). The...

The gas in a rocket combustion chamber is at 120 psia and 1600°R

(Fig. 2.14). The gas expands through an adiabatic frictionless (isentropic)

nozzle to 15 psia. What are the temperature and velocity of the gas leaving

the nozzle? Treat the gas as the calorically perfect gas air with y = 1.4 and

gcCp = 6000 ft2/(s 2. °R)

Engineering   Mechanical-Engineering   
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