Aircraft Engine Performance at Design Point
- Subsonic/Supersonic 1-Spool Turbojet
- Subsonic 2-Spool Turbofan
- Subsonic 2-Spool Boosted Turbofan
- Subsonic 3-Spool Turbofan

- Analysis of the Thermodynamic Cycle
- Nozzle Area and Performance (Thrust Power etc.) calculation
- Mass Flows (Core Bypass Fuel)
- Automatic calculation of ambient conditions based on the flight altitude using the International Standard Atmosphere model
- Automatic calculation of Cp gama R for each component based on temperature and Fuel to Air Ratio
- Automatic calculation of isentropic efficiency for each compressor and turbine based on polytropic efficiency and pressure ratio

Compressor Map Operating Point Prediction using
- Scaling Techniques on an existing HPC map
- Artificial Neural Networks to interpolate the existing map's data

Aircraft Emissions
- Emissions calculation for aircraft engines in LTO cycle and Cruise
- Type of turbofan engines used: 1. Subsonic 2-Spool 2. Subsonic 3-Spool

Hybrid Precooled Rocket Engine at Design Point
- Analysis of the combined Thermodynamic Cycles with Air Hydrogen & Helium as working fluids.