Total Energy At Nozzle Inlet For a Rocket Engine Calculator

The total energy at the nozzle inlet for a rocket engine involves considering the enthalpy and kinetic energy of the propellant before combustion.

This formula combines the static enthalpy, which represents the energy content of the propellant due to its temperature and pressure, and the kinetic energy, which represents the energy associated with the motion of the incoming propellant.

To use this formula, you would need specific values for the static enthalpy and the velocity of the incoming propellant. These values depend on the properties of the propellant, the ambient conditions, and the design of the rocket engine.

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

where,

• E is the Total Energy, i.e sum of kinetic and potential energy
• $h$ is the Static Enthalpy at nozzle Inlet,
• $V$ is the velocity of the incoming air relative to the reference frame of the engine.