In a jet engine, a flow of air at 1000 K, 200 kPa, and 40 m/s enters a nozzle, where the air exits at 500 m/s and 90 kPa. What is the exit temperature, inlet area, and exit area, assuming no heat loss?
min = mout = m
where m = mass air flow
dE/dt cv = Qcv - Wcv + Σmin(h+ (Vin/2)2 + gz) - Σmout(h+ (Vout/2)2 + gz)
m = ρAV
where m = mass air flow, ρ = density, A = area, V = velocity
The Attempt at a Solution
I've already solved for the exit temperature to be 890 K. I just need to know how to find the exit/inlet areas.