Total Energy At Nozzle Exit For a Solid Propellant Rocket Engine Calculator

Solid rocket engines typically use a grain of solid propellant that burns from the inside out, and the burning of the propellant occurs at the exposed surface of the grain. It’s important to note that for solid rocket engines, the specific details of the combustion process and the determination of internal energy depend on the specific formulation of the solid propellant and the combustion characteristics. 

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