Consider a turbojet-powered airplane flying at a velocity of \(300 \mathrm{~m} / \mathrm{s}\) at an altitude of \(10 \mathrm{~km}\), where the free-stream pressure and density are \(2.65 \times 10^{4} \mathrm{~N} / \mathrm{m}^{2}\) and \(0.414 \mathrm{~kg} / \mathrm{m}^{3}\), respectively. The turbojet engine has inlet and exit areas of \(2 \mathrm{~m}^{2}\) and \(1 \mathrm{~m}^{2}\), respectively. The velocity and pressure of the exhaust gas are \(500 \mathrm{~m} / \mathrm{s}\) and \(2.3 \times 10^{4} \mathrm{~N} / \mathrm{m}^{2}\), respectively. The fuel-to-air mass ratio is 0.05 . Calculate the thrust of the engine.