RCAIDE.Library.Plots.Aerodynamics.plot_lift_distribution

plot_lift_distribution

plot_lift_distribution(results, save_figure=False, save_filename='Lift_Distribution', file_type='.png', width=11, height=7)

Generate plots of spanwise lift distribution for lifting surfaces.

Parameters:

• results (Data) –

  Mission results data structure containing:

  • results.segments.conditions.aerodynamics.coefficients.lift with fields:

    • inviscid_wings_sectionalarray

      Sectional lift coefficients at control points

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

• save_filename (str, optional) – Base name for saved figure files, default “Lift_Distribution”

• 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 – Figure showing spanwise lift distribution

Return type:

matplotlib.figure.Figure

Notes

Creates figures showing:

• Sectional lift coefficient (CLy) vs spanwise location

• Separate plot for each timestep in each segment

• Different wings distinguished by line colors:

  • Blue: Main wings

  • Red: Horizontal tails

  • Black: Other surfaces

Definitions

‘Sectional Lift Coefficient’

Non-dimensional lift force per unit span

‘Control Points’

Points where circulation/lift is evaluated

See also

RCAIDE.Library.Plots.Common.set_axes

Standardized axis formatting

RCAIDE.Library.Plots.Common.plot_style

RCAIDE plot styling