Flame Temperature of Combustion in a Saturn V Rocket Engine Calculator

The Saturn V rocket, used during the Apollo program, was a multi-stage liquid-fueled launch vehicle. It used a variety of rocket engines for propulsion, including the F-1 engines on the first stage. These engines burned a combination of liquid oxygen (LOX) and kerosene (RP-1) to generate thrust.

The adiabatic flame temperature T_adiabatic is an estimate of the maximum temperature reached during combustion when no heat is lost to the surroundings. The formula for adiabatic flame temperature is:

Where:

• T_adiabatic: Adiabatic flame temperature (in Kelvin).
• T_inlet​: Inlet air temperature (in Kelvin).
• T_fuel​: Fuel temperature (in Kelvin).
• C_p​: Specific heat at constant pressure (in J/(kg·K)).
• $\gamma$: Ratio of specific heats (C_p​/C_v​).
• $R$: Specific gas constant (in J/(kg·K)).