[img]file:///C:/t/moz-screenshot.jpg[/img][img]file:///C:/t/moz-screenshot-1.jpg[/img][img]file:///C:/t/moz-screenshot-2.jpg[/img][img]file:///C:/t/moz-screenshot-3.jpg[/img] Thx, for bearing with me...
Now, check this shematics.
CP moves until aerodynamic center and that's the furthest point the CP will go.
After that, CP begins to move toward the stall AoA, after which departs wing's chord, resulting in zero lift again (like in the start position).
Now, observe tirquise line (CP) while it leaves wingtip's chord to reach aerodynamic center. You see, that CP's line of lift, will be cropped by leading edge on delta wing. On the straight wing, this doesn't occurs in straight wing, hence the steeper Cl/AoA curve and better spanwise lift distribution, but lower max AoA.
Finally, observe how CP must travel a longer distance in delta wing to reach AC, than in straight one. The pure arrow (Me262, Sabre) wing will be the worst of all, because it'll feature short MAC, but high sweep and therefore large tip moments and a demanding structural integrity to keep it together, while having steep lift curve and be easy to overstress.
Am I correct?
In any case, thanks a lot guys.