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Temp. and Pressure aft combustion

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Old   October 20, 2017, 00:50
Default Temp. and Pressure aft combustion
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Myoungjin Kim
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I'm using nasa cea program(GUI ver) for rocket problem.
In my lab, I'm designing the rocket nozzle, with Al and air under 2Bar atmosphere.

Commonsensically, after combustion, the pressure and temperature would rise. and these value will contribute to the nozzle design parameter such as P0 and T0(the subscript 0 means total properties).

However, if i run the CEA code with given initial pressure(2Bar), the output shows same pressure value, 2Bar. and the error shows that - WARNING!! CALCULATIONS WERE STOPPED BECAUSE NEXT POINT IS MORE THAN 50 K BELOW THE TEMPERATURE RANGE OF A CONDENSED SPECIES (ROCKET) -

If i change the reactant to O2(gaseous species), there are no error messages but the pressure value shows same.

I cant understand why the pressure output after combustion shows the same value.
How can I get the pressure value after combustion?
Attached Files
File Type: txt Al and O2.txt (8.1 KB, 2 views)
File Type: txt Al and Air.txt (11.5 KB, 1 views)
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