AeroEngineS12.8.1

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

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

Ramjet Engine at Design Point
- Simulation of the thermodynamic cycle of a hydrogen fuelled Ramjet engine at optimised conditions.

Turboramjet Engine at Design Point
- Simulation of the thermodynamic cycle of a Turboramjet engine at which operates in high speeds.

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

Compressor Map Operating Point Prediction using
- Scaling Techniques on an existing HPC map
- Artificial Neural Networks to interpolate the existing maps data
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Developer: Aggelos Gaitanis
Original creator: Evangelia Pontika
HyRE, Ramjet tab programmer: Spiros Tsentis
Emissions tab developer/programmer: Maria Bakali
Advisor: Ioanna Aslanidou, Konstantinos Kyprianidis
Supervisor: Anestis Kalfas
AeroEngineS V12.8.1更新日志：
-Design modifications