At 04:12 AM 9/30/04, Gavin wrote: >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.
A paper on load distrubution and how to calculate (close but approximate) the mean aerodynamin chord for a tapered wing is at this link: http://www.bd5.com/BedeDesign15.jpg So, the slightly conservative calculation for bending load on the spar would be half the maximum G-load gross weight of the plane at a lever arm of the MAC distance. Regards, RonB
