Total Energy At Nozzle Exit For a Liquid Propellant Rocket Engine Calculator

In a liquid propellant rocket engine, the nozzle exit is a critical point where the high-speed exhaust gases exit the rocket nozzle into space. The total energy at the nozzle exit is the sum of the enthalpy and kinetic energy of the exhaust gases.

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