Hi all,

I’m a student studying mechanical engineering and struggling with an assignment on analysis on aircraft wing analysis.

We are given wing profile, stiffener and spar data and are asked to determine the stresses in the wing.

Now in the examples of idealised sections we have already completed (fuselages) we are given a load and moment. For this assignment we are not, instead we are given technical data for the A/C which is:

Max take-off weight
Length
Wing span with winglets
Body exterior width
Cruise altitude
Time to reach cruise altitude.

How do I obtain a load and moment to start my idealised section analysis to gain the stresses in the wing, also How will I know exactly where the force will act.

Any help to get me started would be greatly appreciated.