. > >> Because you have added to the length of the wing you have added to the > bending moment at the fuselage (the lift loads are farther from the > fuselage). > I disagree that lift loads are much larger farther from the fuselage on the new 504xx wing designs! Maybe someone can shed some light on this? the chord of the wing decreases as the wing tapers to the tip, therefore reducing the available lift as the wing tapers due to reduces area. Now I know that there is a leverage component added as the wing gets further from the attach fittings but is this compensated for by the reduced wing area as it tapers away? Also it is important to remember that the wing (in the case of the standard KR wing design with a constant chord) doesn't lift the plane at the tip thus producing a huge leverage moment at the tip, the lift is evenly distributed over the span thus trying to lift the wing almost vertically evenly, and not having the so called bending moment as some think. So I wonder if there is more force on the attach fittings in a vertical shear than in a tension and compression scenario as first thought??? Maybe someone can shed some light on this.
Gav
