A bipropellant liquid rocket motor operates at a chamber pressure of 40 bar with a nozzle throat diameter of $50 \mathrm{~mm}$. The characteristic velocity is $1540 \mathrm{~m} / \mathrm{s}$. If the fuel-oxidizer ratio of the propellant is $1.8,$ and the fuel density is $900 \mathrm{~kg} / \mathrm{m}^{3},$ what should be the minimum fuel tank volume for a burn time of 8 minutes

(A) $1.65 \mathrm{~m}^{3}$

(B) $1.75 \mathrm{~m}^{3}$

(C) $1.85 \mathrm{~m}^{3}$

(D) $1.95 \mathrm{~m}^{3}$

A bipropellant liquid rocket motor operates at a chamber pressure of 40 bar with a nozzle throat diameter of $50 \mathrm{~mm}$. The characteristic velocity is $1540 \mathrm{~m} / \mathrm{s}$. If the fuel-oxidizer ratio of the propellant is $1.8,$ and the fuel density is $900 \mathrm{~kg} / \mathrm{m}^{3},$ what should be the minimum fuel tank volume for a burn time of 8 minutes

(A) $1.65 \mathrm{~m}^{3}$

(B) $1.75 \mathrm{~m}^{3}$

(C) $1.85 \mathrm{~m}^{3}$

(D) $1.95 \mathrm{~m}^{3}$

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