RCAIDE.Library.Plots.Geometry.generate_3d_propulsor_points

generate_3d_propulsor_points#

generate_3d_propulsor_points(propulsor, tessellation=24)[source]#

Generates 3D coordinate points that define a propulsor surface.

Parameters:

  • propulsor (Propulsor) – RCAIDE propulsor data structure containing geometry information

  • tessellation (int, optional) – Number of points to use in circumferential discretization (default: 24)

Returns:

G – Data structure containing generated points

  • PTSndarray

    Array of shape (num_segments, tessellation, 3) containing x,y,z coordinates of surface points

Return type:

Data

Notes

Points are generated by creating super-elliptical cross-sections at each segment and positioning them according to segment locations.

Major Assumptions

  • Cross-sections lie in y-z plane

  • Segments are ordered from nose to tail

  • Origin is at the nose of the fuselage

See also

plot_3d_fuselage

Function to visualize the generated surface

generate_points_from_propulsor_geometry(propulsor_geometry, propulsor, tessellation)[source]#
generate_turbofan_geometry(propulsor)[source]#

Generates a geometry data structure for a turbofan propulsor based on its parameters.

Parameters:

propulsor (Turbofan) – RCAIDE turbofan propulsor data structure containing geometry information

Returns:

geometry – Data structure containing geometric segments and properties of the turbofan

Return type:

Data

Notes

The geometry is constructed by defining segments for the fan, core, and nacelle based on the propulsor’s dimensions and locations.

Major Assumptions

  • Segments are defined as super-elliptical cross-sections

  • The origin is at the front of the fan

  • The geometry is symmetric about the centerline

See also

generate_3d_propulsor_points

Function to generate 3D points from the geometry

generate_turbojet_geometry(propulsor)[source]#

Generates a geometry data structure for a turbojet propulsor based on its parameters.

Parameters:

propulsor (Turbojet) – RCAIDE turbojet propulsor data structure containing geometry information

Returns:

geometry – Data structure containing geometric segments and properties of the turbojet

Return type:

Data

Notes

The geometry is constructed by defining segments for the fan, core, and nacelle based on the propulsor’s dimensions and locations.

Major Assumptions

  • Segments are defined as super-elliptical cross-sections

  • The origin is at the front of the fan

  • The geometry is symmetric about the centerline

See also

generate_3d_propulsor_points

Function to generate 3D points from the geometry

generate_turboprop_geometry(propulsor)[source]#

Generates a geometry data structure for a turboprop propulsor.