Total Energy At Nozzle Exit For a Nuclear Thermal Rocket Engine Calculator

A Nuclear Thermal Rocket (NTR) engine is a type of rocket engine that uses nuclear reactions to heat a propellant, typically hydrogen, which is then expelled through a rocket nozzle to produce thrust. In the context of an NTR engine, the term “nozzle exit” refers to the point where the high-speed heated propellant is expelled.

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