Combustion temperature is the temperature in the combustion chamber in degrees Kelvin. The combustion temperature for liquid fueled rockets is typically around six thousand degrees Kelvin. The combustion temperature will be higher if the reaction releases a higher amount of energy, so a fuel reacting with liquid oxygen will reach a higher temperature than a fuel reacting with hydrogen peroxide. The combustion temperature will generally be higher if the exhaust has a higher molecular weight, if it is high in carbon dioxide for instance. The reaction of ethanol and hydrogen peroxide will reach a temperature of about three thousand nine hundred degrees Kelvin. The reaction of quadricyclene and oxygen react will reach a temperature of about seven thousand eight hundred degrees Kelvin.

High combustion temperatures require liquid cooled combustion chambers and nozzle throats. Often these are made of copper because of its high thermal conductivity. Exhaust molar, product enthalpy, reactant enthalpy and temperature change are used to calculate the combustion temperature which is in turn used to calculate the throat temperature.

k = 1.21
temperature change = ( reactant enthalpy - product enthalpy ) * ( 1.0 - 1.0 / k ) / 8,314 J * K / kmol / exhaust molar
combustion temperature = temperature change + 298

throat temperature = combustion temperature / ( 0.5 + 0.5 * k )
 
 

This is used in bipropellant rocket, tripropellant rocket, pumped rocket and rocket cost.
 
 

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