RCAIDE.Library.Plots.Geometry.plot_3d_vehicle_vlm_panelization

plot_3d_vehicle_vlm_panelization#

plot_3d_vehicle_vlm_panelization(vehicle, alpha=1.0, plot_axis=False, save_figure=False, show_wing_control_points=True, save_filename='VLM_Panelization', min_x_axis_limit=-5, max_x_axis_limit=40, min_y_axis_limit=-20, max_y_axis_limit=20, min_z_axis_limit=-20, max_z_axis_limit=20, show_figure=True)[source]#

Creates a 3D visualization of vehicle vortex lattice method (VLM) panelization.

Parameters:

  • vehicle (Vehicle) – RCAIDE vehicle data structure containing geometry information

  • alpha (float, optional) – Transparency value between 0 and 1 (default: 1.0)

  • plot_axis (bool, optional) – Flag to show coordinate axes (default: False)

  • save_figure (bool, optional) – Flag for saving the figure (default: False)

  • show_wing_control_points (bool, optional) – Flag to display VLM control points (default: True)

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

  • min_x_axis_limit (float, optional) – Minimum x-axis plot limit (default: -5)

  • max_x_axis_limit (float, optional) – Maximum x-axis plot limit (default: 40)

  • min_y_axis_limit (float, optional) – Minimum y-axis plot limit (default: -20)

  • max_y_axis_limit (float, optional) – Maximum y-axis plot limit (default: 20)

  • min_z_axis_limit (float, optional) – Minimum z-axis plot limit (default: -20)

  • max_z_axis_limit (float, optional) – Maximum z-axis plot limit (default: 20)

  • show_figure (bool, optional) – Flag to display the figure (default: True)

Returns:

fig – Figure handle containing the generated plot

Return type:

plotly.graph_objects.Figure

Notes

Creates an interactive 3D visualization showing:

  • VLM panels on lifting surfaces

  • Control points (optional)

  • Customizable view and axis limits

If vehicle’s vortex distribution is not available, generates a new one with:

  • 25 spanwise vortices

  • 5 chordwise vortices

  • Linear spanwise spacing

  • No fuselage or nacelle modeling

Major Assumptions

  • Lifting surfaces are represented by flat panels

  • Control points are at 3/4 chord of each panel

  • Vortex lines are at 1/4 chord of each panel

Definitions

‘Control Point’

Location where boundary condition is enforced

‘Vortex Line’

Line of bound vorticity representing lift

‘Panel’

Discrete element of lifting surface