## How to solve for bending moment?

Hello, I'm a newbie here, please help me to solve for the bending moment of my design airplane. I want to know if my wing spar is strong enough to support the weight of my design which is 490 lb. I want also to know if what is the breaking point of the wing spar. Please see the attached picture.

Thank you...
Attached Images
 My Design.bmp (273.6 KB, 17 views)
 Recognitions: Science Advisor You can assuming that your beam is simply supported at the wing tips, with a point load at the center, and then just either simply compute the bending moments in your beam. The stress is then just $$\sigma = \frac{My}{I}$$ Or I'm sure a decent google result will give you the closed form solution given your geometry.