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Category > Applied Sciences Posted 28 Jul 2017 My Price 5.00

A rocket nozzle is designed to expand exhaust gases (R = 300 J/kg/K, k = 1.3) from a chamber pressure

A rocket nozzle is designed to expand exhaust gases (R = 300 J/kg/K, k = 1.3) from a chamber pressure of 600 kPa and total temperature of 3000 K to a Mach number of 2.5 at the exit. The throat area is 0.1 m2.  Find the area at the exit, the exit pressure, the exit velocity, and the mass flow rate.

 

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Alpha Geek
(8)
Status NEW Posted 28 Jul 2017 09:07 AM My Price 5.00

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