Comprehensive aerodynamic design and CFD analysis of a Fixed-Wing UAV, featuring lift/drag coefficient calculations and pressure distribution mapping using OpenVSP.
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## 📌 Project Overview
Complete aerodynamic design and analysis of a Fixed Wing UAV
using OpenVSP for geometry creation and VSPAERO for
aerodynamic simulation. This project demonstrates the full
aerospace engineering workflow from design to analysis.
## 🎯 UAV Specifications
| Parameter | Value |
|---|---|
| Wing Span | 3.0 m |
| Root Chord | 0.4 m |
| Tip Chord | 0.2 m |
| Wing Area | 1.2 m² |
| Fuselage Length | 2.5 m |
| Airfoil | NACA 2412 |
| Cruise Speed | 20 m/s |
| UAV Mass | 2.5 kg |
## 📊 Aerodynamic Results
| Parameter | Value |
|---|---|
| Max Lift Coefficient CL | 0.6621 |
| Min Drag Coefficient CD | 0.0144 |
| Best L/D Ratio | 8.76 |
| Best Angle of Attack | 4.0 degrees |
| Stall Speed | 7.10 m/s |
| Cruise Lift | 65.54 N |
| Cruise Drag | 7.48 N |
## 🛠️ Tools Used
| Tool | Purpose |
|---|---|
| OpenVSP 3.48.2 | UAV geometry design |
| VSPAERO | Aerodynamic analysis |
| Python | Results processing |
| Matplotlib | Data visualization |
## 🗂️ Project Structure
uav-cfd-analysis/
├── geometry/
│ └── UAV_design.vsp3
├── results/
│ ├── aerodynamic_analysis.png
│ ├── cl_curve.png
│ ├── cd_curve.png
│ ├── ld_ratio.png
│ ├── load_distribution.png
│ ├── convergence.png
│ ├── cp_slice.png
│ ├── sweep_results.png
│ └── vspaero_results.csv
├── analyze_results.py
└── README.md
## 📈 Results
### Aerodynamic Analysis
### Lift Coefficient Curve
### Load Distribution
### Drag Polar
## ⚙️ How to Reproduce
1. Install OpenVSP 3.48.2
2. Open geometry/UAV_design.vsp3
3. Run VSPAERO analysis
4. Run analyze_results.py
## 👨💻 Author
Yogesh E S
Aeronautical Engineer | Drone AI Developer