An aircraft with a turbojet engine, having an inlet area of $1 \mathrm{~m}^{2}$, is flying at $270 \mathrm{~m} / \mathrm{s}$ at an altitude where the atmospheric pressure is equal to 0.9 bar and the ambient temperature is equal to $290 \mathrm{~K}$. The stagnation pressure and temperature at the exit of the turbine are equal to 1.6 bar and $774 \mathrm{~K}$ respectively. The specific heat at constant pressure of the burned gases is equal to $1.147 \mathrm{~kJ} / \mathrm{kgK}$ and the ratio of specific heats is equal to 1.33. Considering ideal expansion in the nozzle with no losses, the specific thrust produced by the engine is______________ $\mathrm{Ns} / \mathrm{kg}$ (in one decimal place).

An aircraft with a turbojet engine, having an inlet area of $1 \mathrm{~m}^{2}$, is flying at $270 \mathrm{~m} / \mathrm{s}$ at an altitude where the atmospheric pressure is equal to 0.9 bar and the ambient temperature is equal to $290 \mathrm{~K}$. The stagnation pressure and temperature at the exit of the turbine are equal to 1.6 bar and $774 \mathrm{~K}$ respectively. The specific heat at constant pressure of the burned gases is equal to $1.147 \mathrm{~kJ} / \mathrm{kgK}$ and the ratio of specific heats is equal to 1.33. Considering ideal expansion in the nozzle with no losses, the specific thrust produced by the engine is______________ $\mathrm{Ns} / \mathrm{kg}$ (in one decimal place).

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