RCAIDE.Library.Plots.Aerodynamics.plot_airfoil_polars

plot_airfoil_polars

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

Generate plots of airfoil aerodynamic characteristics from analysis results.

Parameters:

• polar_data (Data) –

  Airfoil analysis results containing:

  • cl_invisc[0]array

    Inviscid lift coefficients

  • cd_invisc[0]array

    Inviscid drag coefficients

  • cm_invisc[0]array

    Inviscid moment coefficients

  • AoA[0]array

    Angles of attack [rad]

  • Re[0]array

    Reynolds numbers

• 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 inviscid airfoil characteristics:

• Top left: Lift coefficient vs angle of attack

• Top right: Drag coefficient vs angle of attack

• Bottom left: Moment coefficient vs angle of attack

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

Results are plotted for a single Reynolds number case, with the Reynolds number shown in the legend (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.compute_airfoil_inviscid

Analysis module

RCAIDE.Library.Plots.Aerodynamics.plot_airfoil_polar_files

Viscous polar plotting function