Aircraft Performance Analysis Tool (MATLAB)

✈️ Overview This project presents a MATLAB-based aircraft performance analysis tool developed as part of my personal engineering portfolio alongside my BEng Aerospace Engineering studies.

The tool models thrust and power required across a range of flight velocities and altitudes using fundamental aerodynamic theory and the International Standard Atmosphere (ISA). The results provide insight into aircraft performance trends and endurance conditions.

🛠 Tools & Skills

• MATLAB
• Aircraft performance fundamentals
• ISA atmospheric modelling
• Data visualisation & engineering interpretation

📐 Engineering Theory Aerodynamic forces are computed using classical relations:

Lift: L = 0.5 · ρ · V² · S · C_L

Drag: D = 0.5 · ρ · V² · S · C_D

For steady, level flight: Thrust Required = Drag
Power Required = Thrust × Velocity

Atmospheric properties are calculated using the ISA tropospheric model (up to 11 km altitude).

▶️ How to Run

1. Open MATLAB
2. Navigate to the src directory
3. Run main.m
4. Generated figures are saved automatically in the figures folder

📈 Results & Insights The final analysis includes:

• Thrust required vs velocity at multiple altitudes
• Power required vs velocity at sea level
• Identification of the best endurance flight condition
• Visual comparison of altitude effects due to air density variation

These results demonstrate how fundamental aerodynamic theory translates into practical aircraft performance analysis.

🔮 Future Improvements

• Drag polar estimation (C_D vs C_L)
• Take-off distance and climb performance
• Multi-aircraft configuration comparison
• Extension to higher-altitude atmosphere models

⚠️ Academic Integrity Notice This project is a personal portfolio work inspired by university-level learning. All problem statements have been generalised and no official coursework questions or assessment solutions are included.