rxmelaun
Automotive
- Sep 20, 2002
- 16
I cannot find a formula for calculating load distribution on a tapered wing. I am calculating deflection of a spar and the formula I'm using (D = WL^4/8EI where D is deflection) assumes that w is a uniform load along the span. I'm not sure if that assumption is correct for the wing design (I do not think it is as the wing has a taper ratio of .48) or if the assumption makes the results pessimistic (actual deflection will be less than calculated) or optimistic (deflection greater than predicted). Obviously, I'd prefer the former or, better still, something resembling reality.
Rich
Rich