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

determine_fuselage_chord(fuselage_width, wing)

Determine chord at wing and fuselage intersection

Assumptions:

Fuselage side of body is between first and second wing segments.

Source:

The Flight Optimization System Weight Estimation Method

Inputs:

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

-.taper: taper ratio -.sweeps.quarter_chord: quarter chord sweep angle [deg] -.thickness_to_chord: thickness to chord -.spans.projected: wing span [m] -.chords.root: root chord [m]

-.fuselages.fuselage.width: fuselage width [m]

Outputs:

chord: chord length of wing where wing intersects the fuselage wall [ft]

Properties Used:

N/A