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_fuel_volume(vehicle[, ...])	Computes the total fuel volume and mass for all fuel tanks in a vehicle.
compute_segment_centroid(le_sweep, seg_span, ...)	Computes the centroid of a trapezoidal segment
compute_segment_meshes(x_in, y_in, x_out, ...)
compute_segment_volume(wing, inner_segment, ...)	Estimate the prism volume between two consecutive wing segments using their airfoil cross-sectional areas and local 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.
fuselage_planform(fuselage[, ...])	Calculates fuselage geometry 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.
wing_planform(wing)	Computes standard wing planform values.