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## Homework Statement

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?

## Homework Equations

*m*

_{in}=

*m*

_{out}=

*m*

where

*m*= mass air flow

dE/dt cv =

*Q*

_{cv}-

*W*

_{cv}+ Σ

*m*

_{in}(h+ (V

_{in}/2)

^{2}+ gz) - Σ

*m*

_{out}(h+ (V

_{out}/2)

^{2}+ gz)

exit area:

*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.