RCAIDE.Library.Methods.Geometry.Planform.wing_planform

wing_planform

wing_planform(wing)

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: 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)

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.

percent_span_unexposed [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