The calculation of total energy at the nozzle inlet for an aerospike engine involves considering the enthalpy and kinetic energy of the propellants or combustion products before entering the nozzle. Aerospike engines are unique in design and feature a bell-shaped nozzle with an annular shape, providing thrust vectoring benefits.
The specific values for these parameters depend on the combustion process, the properties of the propellants, the design characteristics of the aerospike engine, and the operating conditions. Detailed information about the specific aerospike engine would be required for precise calculations.
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