An end burning rocket motor has a chamber diameter of 10 cm and a nozzle exit diameter of 8 cm The density of the solid propellant is 1770 kg m 3 , and the propellant surface regresses at the rate of 1 2 cm s The gases crossing the nozzle exit plane have a pressure of 10 kPa abs and a temperature o...

Given inlet diameter d 1 10 cm 01 m exit diameter d 2 8 cm 008 ...

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

Question:

An end-burning rocket motor has a chamber diameter of 10 cm and a nozzle exit diameter of 8 cm. The density of the solid propellant is 1770 kg/m³, and the propellant surface regresses at the rate of 1.2 cm/s. The gases crossing the nozzle exit plane have a pressure of 10 kPa abs and a temperature of 2200°C. Th e gas constant of the exhaust gases is 415 J/kg K. Calculate the gas velocity at the nozzle exit plane.