A turbojet-powered aircraft is flying at 240 m/s and 7000-m altitude, where the ambient temperature and pressure are 240 K and 41 kPa, respectively. The pressure ratio of the compressor is 6 and the turbine inlet temperature is 970 K. At these conditions, the fuel flow rate is 0.68 kg/s and the overall air– fuel ratio is 75:1. Estimate the thrust developed by the engine. Also determine the specific thrust, the specific fuel consumption, and the propulsive efficiency. Employ an air-standard-cycle analysis using the constant-pressure specific heat c_p and specific-heat ratio γ for air and neglecting the fuel properties.