To calculate the total energy at the nozzle inlet for a specific rocket engine, such as the RD-170, detailed information about the propellant, combustion process, and design characteristics of that particular engine is required.
To obtain accurate values for the RD-170 engine, you would need to refer to the specific technical documentation or engineering data provided by the engine manufacturer or the relevant space agency.
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
- Â is the Static Enthalpy at nozzle Inlet,
- Â is the velocity of the incoming air relative to the reference frame of the engine