RCAIDE.Library.Methods.Mass_Properties.Weight_Buildups.Conventional.BWB.FLOPS.compute_bwb_wing_weight.generate_wing_stations

generate_wing_stations(fuselage_width, wing)

Divides half the wing in sections, using the defined sections

and adding a section at the intersection of wing and fuselage

Assumptions:

Source:

The Flight Optimization System Weight Estimation Method

Inputs:

fuselage_width: fuselage width [m] wing: data dictionary with wing properties

-.taper: taper ration wing -.sweeps.quarter_chord: quarter chord sweep angle [deg] -.thickness_to_chord: thickness to chord -.spans.projected: wing span [m] -.chords.root: root chord [m] -.tip.root: tip chord [m] -.twists.root: twist of wing at root [deg] -.twists.tip: twist of wing at tip [deg] -.Segments: trapezoidal segments of the wing

Outputs:

ETA: spanwise location of the sections normalized by half span C: chord lengths at every spanwise location in ETA normalized by half span T: thickness to chord ratio at every span wise location in ETA SWP: quarter chord sweep angle at every span wise location in ETA

Properties Used:

N/A