User:Eas4200c.f08.gator.edwards/Wk5 Matlab

This MATLAB program calculates the maximum bending moments, maximum normal bending stresses, and ultimate moments for an airfoil and stringers. Part 1 uses only the four sets of stringers while Part 2 uses the stringers and the skin. The figure shows the centroid of the stringers, the total centroid, and the neutral axis, along with the airfoil outline and spars.

The results show around a 6% increase in ultimate moment between Parts 1 and 2. This is a fairly small amount so the approximation of using only the stringers is good for many applications. The maximum normal bending stress is two orders of magnitude higher in Part 2, indicating an error in the calculations