A rocket engine has a sea level specific impulse of $210 \mathrm{~s}$ and a nozzle throat area of $0.005 \mathrm{~m}^{2}$. While testing at sea level conditions, the characteristic velocity and pressure for the thrust chamber are $1900 \mathrm{~m} / \mathrm{s}$ and 50 bar, respectively. Assume the acceleration due to gravity to be $9.8 \mathrm{~m} / \mathrm{s}^{2}$. The thrust produced by the rocket engine is_______________ $\quad \mathrm{kN}$ (round off to one decimal place).

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A rocket engine has a sea level specific impulse of $210 \mathrm{~s}$ and a nozzle throat area of $0.005 \mathrm{~m}^{2}$. While testing at sea level conditions, the characteristic velocity and pressure for the thrust chamber are $1900 \mathrm{~m} / \mathrm{s}$ and 50 bar, respectively. Assume the acceleration due to gravity to be $9.8 \mathrm{~m} / \mathrm{s}^{2}$. The thrust produced by the rocket engine is_______________ $\quad \mathrm{kN}$ (round off to one decimal place).