RCAIDE.Library.Methods.Geometry.Planform

Planform

RCAIDE Package Setup

Modules

compute_chord_length_from_span_location(...)	Computes the chord length given a location along the half-span.
compute_span_location_from_chord_length(...)	Computes the location along the half-span given a chord length.
convert_sweep(wing[, ...])	This method converts the sweep of a wing planform to refer to a new chord fraction.
estimate_wing_internal_volume
fuselage_planform(fuselage[, ...])	Calculates fuselage geometry values
horizontal_tail_planform(Wing)	Calls generic wing planform function to compute wing planform values
horizontal_tail_planform_raymer(...)	Adjusts reference area before calling generic wing planform function to compute wing planform values.
populate_control_sections(wing)	This function takes the control surfaces defined on a wing and appends them to wing segments Conditional statements are used to determine where the control surface bounds are in relation to the wing segments.
vertical_tail_planform(Wing)	Calls generic wing planform function to compute wing planform values
vertical_tail_planform_raymer(...)	Adjusts reference area before calling generic wing planform function to compute wing planform values.
wing_fuel_volume(wing)	Calculates the available fuel volume in a wing.
wing_planform(wing)	Computes standard wing planform values.
wing_segmented_planform(wing[, ...])	Computes standard wing planform values.