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Category > Applied Sciences Posted 04 Jun 2017 My Price 3.00

An end-burning rocket motor has a chamber diameter of 10 cm

An end-burning rocket motor has a chamber diameter of 10 cm and a nozzle exit diameter of 8 cm. The density of the propellant is 1750 kg/m3, and the surface regresses at the rate of 1 cm/s. The gases crossing the nozzle exit plane have a pressure of 10 kPa abs and a temperature of 2200°C. The gas constant of the exhaust gases is 415 J/kg K. Calculate the gas velocity at the nozzle exit plane.

 

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Alpha Geek
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Status NEW Posted 04 Jun 2017 06:06 AM My Price 3.00

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