I'm building a rocket engine and need to know the temperature of the gases inside the combustion chamber (ie the stagnation temperature).
The combustion chamber pressure is 5 atmospheres. The engine works with ethanol and pure oxygen (inlet pressure: 10atm; levels out to 5atm once in the chamber) mixed at a perfect stoichiometric ratio.
For now, knowing the adiabatic flame temperature of ethanol under these conditions will suffice ie I don't need to take into account dissociation effects or the heat sinking properties of the metal walls of the combustion chamber.
My research has shown that one has to do the following in order to calculate the adiabatic flame temperature:
Set up an equation with the sum of enthalpies of all reactants on one side, and the sum of enthalpies of products on the other.
Enthalpy is a function of temperature. Therefore, in order to find the enthalpy of the products, one will have to experiment with different values for the temperature until the equation is equalized.
The value for the temperature that satisfies the equation is the adiabatic flame temperature.
I used this site primarily as a reference: http://braeunig.us/space/thermo.htm
The issue is, however, that enthalpy is actually a function of not only temperature, but pressure too. The site mentioned above however assumes that the pressure of the products is 1atm ie 0.1 MPa (aka reference pressure). In other words, its calculations don't apply to my case, as my combustion occurs in a much higher pressure environment.
How is the enthalpy of a substance at a given pressure & temperature calculated? Alternatively, where can I find tables that document this data if calculations aren't possible? I'm still too young to have an advanced background in thermodynamics, so please take it easy on me. I appreciate any help. Thank you!