Aturbojet engine flying at m = 0.7 ingests an airflow of 5.2 kg/s. the mach numbers at the entrance and exit of the inlet are 0.45 and 0.3 respectively. ambient temperature and pressure are 200 k and 1000 pa (n/m2) respectively. the inlet stagnation pressure ratio rd= p02/p01 = 0.95. assume ï§ = 1.4 and r = 287 j/kg k.

a)what are the stagnation temperature and pressure at the entrance to the inlet?

b)what is the static pressure at the entrance to the inlet?

c)what are the stagnation and static pressures at the exit of the inlet?

d)what is the area of the entrance to the inlet?

e)what is the capture area (i. e., the area of the flow far ahead of the engine that enters the inlet)?