Calculate the stagnation temperature (K) at the exit from the fan.
A jet aircraft is flying at a true airspeed of 220 m/s in ISA conditions at an altitude of 5500 m.
Propulsion for this aircraft is provided by two small turbofan engines, each of which, at this flight operating condition, has a core mass flow of 5.1 kg/s, a bypass ratio of 3.3, a fan pressure ratio of 1.58, and a fan polytropic efficiency of 91.2%.
It may be assumed that:
- Intake isentropic efficiency = 93%
- There are no pressure losses in the bypass duct
- The bypass flow propelling nozzle area is matched to this operating condition.
- For air, γ = 1.4, R = 0.287 kJ/kg·K