RCAIDE.Library.Methods.Geometry.Planform.wing_segmented_planform

wing_segmented_planform

wing_segmented_planform(wing, overwrite_reference=False)

Computes standard wing planform values.

Assumptions: Multisegmented wing. There is no unexposed wetted area, ie wing area that intersects inside a fuselage. Aerodynamic center is at 25% mean aerodynamic chord.

Source: None

Inputs: overwrite_reference <boolean> Determines if reference area, wetted area, and aspect

ratio are overwritten based on the segment values.

wing.

chords.root [m] spans.projected [m] symmetric <boolean> Determines if wing is symmetric

Outputs: wing.

spans.total [m] chords.tip [m] chords.mean_aerodynamics [m] wing.chords.mean_geometric [m] areas.reference [m^2] taper [-] sweeps.quarter_chord [radians] aspect_ratio [-] thickness_to_chord [-] dihedral [radians]

aerodynamic_center [m] x, y, and z location

Properties Used: N/A

segment_properties(wing, update_wet_areas=False, update_ref_areas=False)

Computes detailed segment properties. These are currently used for parasite drag calculations.

Assumptions: Segments are trapezoids

Source: http://aerodesign.stanford.edu/aircraftdesign/aircraftdesign.html (Stanford AA241 A/B Course Notes)

Inputs: wing.

exposed_root_chord_offset [m] symmetric [-] spans.projected [m] thickness_to_chord [-] areas.wetted [m^2] chords.root [m] Segments.

percent_span_location [-] root_chord_percent [-]

Outputs: wing.areas.wetted [m^2] wing.areas.reference [m^2] wing.segments.

taper [-] chords.mean_aerodynamic [m] areas.

reference [m^2] exposed [m^2] wetted [m^2]

Properties Used: N/A

segment_centroid(le_sweep, seg_span, dx, dy, dz, taper, A, dihedral, root_chord, tip_chord)

Computes the centroid of a trapezoidal segment

Assumptions: Polygon

Source: None

Inputs: le_sweep [rad] seg_span [m] dx [m] dy [m] taper [dimensionless] A [m**2] dihedral [radians] root_chord [m] tip_chord [m]

Outputs: cx,cy [m,m]

Properties Used: N/A