CD Nozzle flow
 

"Hi
I am solving a problem on nozzle flow..i was analysing the results..i am actually using a CFD software for analysis..i am observing that for my chamber pressure of 56bar and chamber temperature of 3500K, the rocket if firing in space...i am getting the exhaust temperature of around 218K, is that low value possible?...my area ratio is around 115. Also I am seeing no change in the exhaust velocities even if I am maintaining the wall temperature of the nozzle(convergent+divergent+chamber) at different values each time say, 0K, 250K, 500K or even 850K. Is that possible?...my wall thickness is 2 mm. Am I fundamentally wrong in some physics?..Please comment."