Flame Temperature of Combustion in a RD 170 Rocket Engine Calculator

The RD-170 is a liquid rocket engine designed and produced in Russia. Specifically, it is a staged combustion cycle rocket engine. It’s part of the family of rocket engines developed by NPO Energomash. For staged combustion cycle engines, the combustion process is more complex than in traditional rocket engines, and the adiabatic flame temperature can be a key parameter.

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)).