Total Energy At Nozzle Inlet in Terms of Specific Energy 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. In the context of rocket propulsion, this energy is often expressed in terms of specific energy, which is the energy per unit mass of the propellant.

Formula for Specific Energy ($e$) at Nozzle Inlet:

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.