How to solve for bending moment?

airstrike_ola

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...

minger

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
[tex]
\sigma = \frac{My}{I}
[/tex]

Or I'm sure a decent google result will give you the closed form solution given your geometry.

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minger 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 [tex] \sigma = \frac{My}{I} [/tex] Or I'm sure a decent google result will give you the closed form solution given your geometry.