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