A turbofan engine has a fan and LPC driven by the LPT. It operates at a flight velocity of 200 m/s at 12,000 m altitude, where the ambient temperature and pressure are 216.65 K and 0.1933 bar, respectively. The overall pressure ratio of the engine is 19, the fan and LPC pressure ratios are 1.65 and 2.5 respectively. The fan, compressors, and turbines have a 90% polytrophic efficiency. Assume an isentropic inlet and separate isentropic convergent nozzles, a fuel heating value of 43,000 kJ/kg, and a combustor total pressure loss of 6.5%. Determine the core engine and bypass duct exit velocities, the engine TSFC, thrust and specific thrust for an engine inlet air flow of 100 kg/s and BPR of 3.0. Determine whether the nozzles are choked.