AeroEngineS

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.