Total Energy At Nozzle Exit For a Cold Gas Propulsion Rocket Engine Calculator

In a cold gas propulsion rocket engine, the term “nozzle exit” refers to the point where the pressurized gas is expelled from the rocket nozzle to generate thrust. Unlike in combustion-based rocket engines, cold gas propulsion involves the release of compressed gas without combustion.

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 static enthalpy at the nozzle exit,
• $V$ is the velocity of the exhaust gases relative to the reference frame of the exhaust gases