Guys, thx a lot for helping.

Phew...I've been through a good two dozens of sites and I think, I got somewhere. So, it turns out that fixed CP concept works for symmetrical, but not cambered wings. Further, it also seems, that in reality the CP for CL=0 isn't in the infinity, but just outside the trailing edge, meaning for zero lift as the CP departed lifting area and that's the correlation with chord I was looking for.
Well, I remembered it was working something like this, but wasn't sure exactly how. It's good though to use movable CP in sense of proving AOA limit depends on chord length, because it's easy to remember, being visually logical concept.
One other thing. For delta wings, the stall occures more gentle than with trapeziodal ones. With the "traveling" CP, it's easily explainable, because as the CP moves forward, it reduces lifting area from the tip towards the root, by exiting the wing's lift area (going ahead of leading edge). OTOH, in trapezoidal wing, the CP is either inside the wing's lifting area, or is out, so the transition is more violent and that corresponds with high AR wings having steeper Cl/AOA curve than lower AR wings.
Ok, I hope this makes sense.

Cheers,Cola