The calculation of total energy at the nozzle throat for a solid propellant rocket engine involves considerations of the energy associated with the propellant before combustion and the kinetic energy of the combustion products.
Keep in mind that this is a simplified approximation, and the actual values would depend on the detailed properties and behavior of the specific solid propellant used.
The total energy () at the nozzle Inlet can be expressed as:
where,
- E is the Total Energy, i.e sum of kinetic and potential energy
- is the Heat of formation of propellant
- Â is the velocity of the incoming air relative to the reference frame of the engine.