A rocket motor has a chamber pressure of 100 bar and chamber temperature of $3000 \mathrm{~K}$. The ambient pressure is 1 bar. Assume that the specific heat at constant pressure is $1 \mathrm{~kJ} / \mathrm{kg}-\mathrm{K}$. Also assume that the flow in the nozzle is isentropic and optimally expanded. The exit static temperature in $\mathrm{K}$ is

(A) 805

(B) 845

(C) 905

(D) 945

A rocket motor has a chamber pressure of 100 bar and chamber temperature of $3000 \mathrm{~K}$. The ambient pressure is 1 bar. Assume that the specific heat at constant pressure is $1 \mathrm{~kJ} / \mathrm{kg}-\mathrm{K}$. Also assume that the flow in the nozzle is isentropic and optimally expanded. The exit static temperature in $\mathrm{K}$ is

(A) 805

(B) 845

(C) 905

(D) 945

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