A gas turbine operates at a pressure ratio of 8 . The air flows into the compressor at \(290 \mathrm{~K}\) and flows out of the combustion chamber at \(1400 \mathrm{~K}\). The efficiency of compressor and turbine are 0.8 and 0.9 respectively. A heat exchanger with effectiveness of 0.85 is used. Assuming an isentropic process, calculate the thermal efficiency and net power output of the engine. The mass flow rate is \(1 \mathrm{~kg} / \mathrm{s}\). Take heat capacity ratio \(\kappa_{\text {air }}=1.38 ; c_{p}=1.005 \mathrm{~kJ} / \mathrm{kgK}\). \([0.61,653.9 \mathrm{~kW}]\)