This project is a Python-based tool developed for preliminary aircraft performance analysis. It evaluates key flight parameters such as range, endurance, lift, drag, and longitudinal dynamics.
- Range and endurance estimation
- Lift and drag calculation
- Weight and center of gravity evaluation
- Acceleration, velocity, and distance computation
- Lift-to-drag (L/D) ratio analysis
The model is based on simplified aerodynamic and flight mechanics equations:
- Lift = 0.5 * CL * rho * V² * S
- Drag = 0.5 * CD * rho * V² * S
- Weight = m * g
- Acceleration = (Thrust - Drag) / Mass
Assuming steady level flight, vertical forces are balanced (Lift ≈ Weight), and acceleration is computed along the longitudinal axis.
- Range: 3000 miles
- Endurance: 20 hours
- Lift: 183750 N
- Drag: 12250 N
- Lift-to-Drag Ratio: 15
- Acceleration: 0.4 m/s²
The model demonstrates how aerodynamic efficiency (L/D ratio) and thrust-to-drag balance directly influence aircraft acceleration and overall performance.
By adjusting input parameters, different flight conditions can be simulated, making this tool useful for preliminary design analysis.
This model uses simplified assumptions and constant parameters. Results are intended for educational and preliminary engineering analysis.
- Python
- NumPy
- Include mission profiles
- Introduce user input interface
Simone Muscolino
Aerospace Engineering Student