RCAIDE.Library.Plots.Geometry.plot_3d_wing

plot_3d_wing#

plot_3d_wing(plot_data, wing, number_of_airfoil_points=21, color_map='greys', alpha=1)[source]#

Creates a 3D visualization of wing surfaces including symmetric sections if applicable.

Parameters:

  • plot_data (list) – Collection of plot vertices to be rendered

  • wing (Wing) – RCAIDE wing data structure containing geometry information

  • number_of_airfoil_points (int, optional) – Number of points used to discretize airfoil sections (default: 21)

  • color_map (str, optional) – Color specification for wing surface (default: ‘greys’)

  • alpha (float, optional) – Transparency value between 0 and 1 (default: 1)

Returns:

plot_data – Updated collection of plot vertices including wing surfaces

Return type:

list

Notes

Creates wing visualization by:

  • Generating points for each segment

  • Creating surface panels between sections

  • Adding symmetric wing if specified

Major Assumptions

  • Wing segments are ordered from root to tip

  • Airfoil sections lie in x-z plane

  • Symmetric wing is mirror image about y-axis

generate_3d_wing_points(wing, n_points, dim)[source]#

Generates 3D coordinate points that define a wing surface.

Parameters:

  • wing (Wing) – RCAIDE wing data structure containing geometry information

  • n_points (int) – Number of points used to discretize airfoil sections

  • dim (int) – Number of wing segments plus one

Returns:

G –

Data structure containing generated points with attributes:
  • X, Y, Zndarray

    Raw coordinate points

  • PTSndarray

    Combined coordinate array

  • XA1, YA1, ZA1, XA2, YA2, ZA2ndarray

    Leading edge surface points

  • XB1, YB1, ZB1, XB2, YB2, ZB2ndarray

    Trailing edge surface points

Return type:

Data

Notes

Generates wing geometry by:

  1. Creating airfoil sections at specified span positions

  2. Applying twist, sweep, and dihedral

  3. Scaling sections by local chord

  4. Positioning in aircraft coordinate system

Definitions

‘Leading Edge Sweep’

Angle between leading edge and y-axis

‘Quarter Chord Sweep’

Angle between quarter chord line and y-axis

‘Dihedral’

Upward angle of wing from horizontal