You should get the internal forces diagram. I guess what my question was is that is just an I beam and I don't know what direction you're trying to march in. You could march down the wing or you could march down the fuselage.
I'm expecting something like you're trying to march spanwise down the 1/4 chord of the swept and tapered wing. Thus, the start is at the centerline=[100,0,0] and the end is at the wingtip=[150,200,0]. The the output coordinate axes march down the wing, but are rotated relative to the direction of integration and align with the global coordinate system.
Could you also add some CAERO1s (for the wing and tail) and a CROD (for the fuselage) to indicate geometry?