The total energy at the nozzle exit of a rocket is the sum of the kinetic energy and the specific enthalpy of the exhaust gases per unit mass. This energy represents the energy content of the exhaust gases as they leave the rocket nozzle. In the context of rocket propulsion, it is often expressed in terms of specific energy, which is the energy per unit mass of the exhaust gases.
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)