Total Energy At Nozzle Exit For a Methane Rocket Engine Calculator

In the context of a methane rocket engine, the “nozzle exit” is the point where high-speed combustion products, including water vapor and carbon dioxide, exit the rocket nozzle. The total energy per unit mass at the nozzle exit can be expressed as the sum of the enthalpy and kinetic energy of the combustion products.

The total energy ($E$) at the nozzle exit can be expressed as:

where,

• E is the Total Energy, i.e sum of kinetic and potential energy
• $h$ is the static enthalpy at the nozzle exit,
• $V$ is the velocity of the exhaust gases relative to the reference frame of the exhaust gases