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Airfoil Flow Analysis with Wind Tunnel Validation

Welcome to the Airfoil Flow Analysis project repository! This software computes essential aerodynamic coefficients for airfoil profiles using a robust panel method approach in Python. It accurately predicts Cp (Coefficient of pressure), Cl (lift), and Cd (drag), and provides insightful visualizations of velocity streamlines.

Features:

  • Panel Method Implementation: Utilizes a subdivision technique for precise aerodynamic calculations.
  • Geometry Generation: Includes an embedded NACA airfoil generator for versatile shape configurations.
  • Integration with XFoil: Seamless integration with XFoil for enhanced accuracy and validation.
  • Streamline Visualization: Generates graphical representations of flow streamlines for intuitive analysis.

Wind Tunnel Integration:

To complement the software's accuracy, a small-scale wind tunnel has been constructed. This setup includes:

  • Test Section Specifications: 0.3m x 0.3m with a 9:1 contraction ratio.
  • Measurement Capabilities: Arduino-based system for real-time data logging of lift, drag, and Cp polars.
  • Experimental Validation: Validates software predictions against empirical data with a high degree of correlation (within 15% error margin).

For more details on the wind tunnel design and integration, visit ldak.dev/projects/wind-tunnel/wind-tunnel.

Usage

Note that to run on Linux, you need to have wine installed (see xfoil.py)

All the required configuration is found in config.txt:

# foil computation
naca_foil: 4412          # 4-digit NACA complient code
angle_of_attack: 0
panel_number: 500        # number of panels used for approximation
v_infinity: 1            # air velocity
grid_size_x: 150
grid_size_y: 150
streamline_comp: True    # set to False to skip expensive and slow streamline computation

# show plot options (they will be saved either way)
foilgen_plot: False
panel_plot: False
cp_plot: False
cp_comparaison: False
streamline_plot: False

# xfoil args
xfoil_run: True

# default values (no need to change them unless you know what you're doing)
panel_bunching: 4
te/le_density: 1
panel_density: 1
top_y/c_lim: 1 1
bottom_y/c_lim: 1 1

Future Developments:

Continued efforts are focused on:

  • Enhancing Computational Efficiency: Optimizing code for faster calculations and expanded modeling capabilities.
  • Improving Accuracy: Refining algorithms for more precise aerodynamic predictions across various airfoil shapes.

Feel free to explore and contribute!