Using the GasEq software, calculate the combustion temperature $($also known as the adiabatic flame temperature$)$ of a CH$4$ O$2$ rocket thrust chamber with r $=4.$ The combustion chamber pressure is $68$ atm. The reactants enter it at $298\mathrm{.}15$ K$.$ Also, list the species formed by the reaction. Ignore any species with a mole fraction less than $0\mathrm{.}01.$

$\{$Partial Ans.: T$=3625$ K$\}$