High-Lift STOL Aerodynamics Pipeline

Project Overview

This project establishes a multi-fidelity aerodynamic analysis pipeline designed to optimize a high-lift wing for regional Short Take-Off and Landing (STOL) aircraft.

Moving beyond manual iteration, this workflow integrates Python-based automation for rapid design space exploration with Industrial CFD for physics validation. The goal was to design a clean-sheet wing capable of high-efficiency cruise ($L/D > 15$) while maintaining the high $C_{L_{max}}$ required for short-field operations.

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The Engineering Pipeline

The project follows a "Crawl, Walk, Run" engineering methodology:

Phase 1: Automated Low-Fidelity Design (Python & XFOIL)

• Tools: Python, AeroSandbox, NeuralFoil
• Method: Developed a script to perform parametric sweeps of flap deflection angles ($0^\circ$ to $30^\circ$) and Angles of Attack.
• Outcome: Automated 80+ simulations in under 10 seconds, selecting the NACA 4412 airfoil for its superior camber characteristics and identifying a 65% increase in $C_{l_{max}}$ with flaps deployed.

Phase 2: 3D Sizing & Induced Drag (OpenVSP)

• Tools: OpenVSP, VSPAERO (Vortex Lattice Method)
• Method: Extruded the optimized section into a finite wing ($b=12m$, $c=1.5m$) to model 3D effects.
• Outcome: Quantified wingtip vortex generation and induced drag penalties, optimizing the planform to a straight-wing configuration to ensure favorable root-to-tip stall progression.

Phase 3: High-Fidelity Validation (Ansys Fluent)

• Tools: Ansys Workbench, DesignModeler, Fluent
• Method: RANS CFD simulation using the SST $k-\omega$ turbulence model with a hybrid mesh (inflation layers for boundary layer resolution).
• Outcome: Validated the final aerodynamic forces at cruise velocity (40 m/s), confirming no premature flow separation.

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Key Results

The multi-fidelity analysis successfully validated the wing's performance against regional transport targets.

Performance Metric	Value	Unit	Condition
Lift Force	4,027	N	Cruise (0° AOA)
Drag Force	218.5	N	Total Viscous + Pressure
Lift Coefficient ($C_L$)	0.228	-	3D Finite Wing
L/D Efficiency	18.43	-	Highly Efficient

Visual Validation

1. RANS CFD Velocity Field Visualization of flow acceleration over the suction surface and stagnation point at the leading edge. Velocity Contour

2. RANS CFD Pressure Field Visualization of pressure distribution over the suction surface and stagnation point at the leading edge. Pressure Contour

3. WingTip Vortex Visualisation Visualization of vortex generated at the wingtip (distribution of particles) [] WingTip Vortex

4.1. Automated Lift Curve Sweep

4.2. Automated Lift Curve Sweep with flaps Lift Curve of Wing with Flaps / Elevators

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📂 Repository Structure

├── 📂 cad and cfd files 
│   ├── STOL_Wing.stp          # Final Clean-Sheet Wing Geometry (STEP)
│   └── STOL_Wing.vsp3         # OpenVSP parametric model
├── 📂 scripts
│   ├── stol_pipeline.py       # Main automation script (AeroSandbox)
│   └── lift_curve_gen.py      # Data visualization script
├── 📂 cfd_results
│   ├── Velocity_Contour.png   # High-Res CFD visualization
│   └── Lift_Drag_Report.txt   # Raw Fluent output data
└── README.md

 ## 📄 License

This project is licensed under the MIT License - see the [LICENSE](LICENSE) file for details.