Need help finding the exhaust temperature of a turbojet engine...?

Question:
I got a homework problem,

Consider a turbojet in an airplane flying at standard sea level conditions with a velocity of 800 ft/s. The pressure ratio across the compressor is 12.5:1. The fuel to air ratio is .05. The nozzle exhausts flow to ambient pressure. Find the temperature of the exhaust. Assuming that the air in the diffuser is slowed to a very low velocity before entering the compressor and the heat released per pound of fuel is 1.4x10^7 ft lb/lbm.

Sea level conditions are :
temperature =518.69 degrees R
pressure = 2116.2 lb/sq ft

Answers:
roughly 700 degrees celsus :) I dont have my engine engineering books to provide calculations. my tuerboprop helicopter engine varies between 670 and 770 degrees celsius
And the answer isssssssssssssssssssssssssss??...

Which engine?
BTW EGT is wayyyy out of style. Now it's T4 or TIT or (Depends on the engine) some other location.
EGT was a very inaccurate place to take the temp. it was at the outlet and not very good (But the best we had at the time.
Now it is still used in piston engines
Good for you if you can figure this one out. For us idiot jet jocks they were kind enough to put an EGT Gage for each engine right there in front of us. EGT means exhaust gas temperature by the way. Now if they'd just stop confusing the issue with this Celsius and Fahrenheit stuff.
first of all EGT is a term used with recip engines I think you mean ITT

ITT = Inlet turbine temprature

EGT = Exhaust Gas Temprature

I think you question is a bit backwards. the air is compressed before it reaches the difusser . the difusser is located after the last stage of compession.
Folks, the question is about Exhaust gas temp, not turbine inlet temp. EGT is the proper guage to use. Even if you could figure out the answer to the question, it all depends on where the EGT is placed. Closer to the engine the hotter it will be. Move it back a few inches and it may be 100 degrees cooler.
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