The given diagram represents the velocity triangles at the leading edge (1) and trailing edge (2) at the mean radius of a single stage axial compressor rotor. The stage efficiency of the compressor is 0.8. The stagnation temperature of air entering the stage is $298 \mathrm{~K}$ and the specific heat at constant pressure for air is $1.005 \mathrm{~kJ} / \mathrm{kgK}$. The ratio of specific heats for air is 1.4. Considering actual work in the rotor is equal to the ideal work, the pressure ratio for the stage is equal to ___________(in two decimal points).

The given diagram represents the velocity triangles at the leading edge (1) and trailing edge (2) at the mean radius of a single stage axial compressor rotor. The stage efficiency of the compressor is 0.8. The stagnation temperature of air entering the stage is $298 \mathrm{~K}$ and the specific heat at constant pressure for air is $1.005 \mathrm{~kJ} / \mathrm{kgK}$. The ratio of specific heats for air is 1.4. Considering actual work in the rotor is equal to the ideal work, the pressure ratio for the stage is equal to ___________(in two decimal points).

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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