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.
The equation we get for Total Energy At Nozzle Exit In Terms of Specific Energy and Specific Impulse is:
where,
- Specific energy (): Joules per kilogram (J/kg)
- Velocity (): Meters per second (m/s)
- Specific impulse (): Seconds (s)
- Acceleration due to gravity (): Meters per second squared (m/s2)