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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


Question ID - 1 | Toppr Answer

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

1 Answer - 5876 Votes

3537

Answer Key : (A) -

(A) 805



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