RCAIDE.Library.Plots.Aerodynamics.plot_airfoil_polar_files

plot_airfoil_polar_files

plot_airfoil_polar_files(polar_data, save_figure=False, save_filename='Airfoil_Polars', file_type='.png', width=11, height=7)

Generate plots of airfoil performance data from polar files.

Parameters:

• polar_data (Data) –

  Airfoil polar data structure containing:

  • lift_coefficientsarray

    CL values for each Reynolds number and angle of attack

  • drag_coefficientsarray

    CD values for each Reynolds number and angle of attack

  • angle_of_attacksarray

    Angles of attack [rad]

  • reynolds_numbersarray

    Reynolds numbers

  • re_from_polararray

    List of Reynolds numbers from polar files

• save_figure (bool, optional) – Save figure to file if True, default False

• save_filename (str, optional) – Name for saved figure file, default “Airfoil_Polars”

• file_type (str, optional) – File extension for saved figure, default “.png”

• width (float, optional) – Figure width in inches, default 11

• height (float, optional) – Figure height in inches, default 7

Returns:

fig

Return type:

matplotlib.figure.Figure

Notes

Creates a 2x2 subplot figure showing airfoil performance:

• Top left: Lift coefficient vs angle of attack

• Top right: Drag coefficient vs angle of attack

• Bottom left: Drag polar (CL vs CD)

• Bottom right: Lift-to-drag ratio vs angle of attack

Each Reynolds number case is plotted in a different color using the inferno colormap. Legend entries show Reynolds numbers in scientific notation (e.g., “Re=1.0e6”).

See also

RCAIDE.Library.Plots.Common.set_axes

Standardized axis formatting

RCAIDE.Library.Plots.Common.plot_style

RCAIDE plot styling

RCAIDE.Library.Analysis.Aerodynamics.process_airfoil_polars

Analysis module