Total Energy At Nozzle Inlet Calculator

The total energy at the nozzle inlet of a rocket is the sum of the kinetic energy and specific enthalpy of the propellant (fuel and oxidizer) per unit mass before it undergoes combustion and expansion in the rocket engine.

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 specific enthalpy of the exhaust gases,
• $V$ is the velocity of the exhaust gases.