RCAIDE.Library.Plots.Geometry.generate_3d_fuel_tank_points.generate_integral_wing_tank_points#

generate_integral_wing_tank_points(wing, n_points, segment_list, fuel_tank, plot_centerline=False)[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

  • plot_centerline (bool, optional) – Include the root centerline cap section in the output, default False

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