Why is the centre of pressure for a real wing with low aspect ratio more forward than that in two-dimensional flow?
The center of pressure is defined as the point on the wing/airfoil where there is a zero net moment. This definition means that it is a function of the lift and subsequently of the lift coefficient. Airfoil theory overestimates the slope of the lift curve due to the absence of wing tip effects. With regards to the second question - I think the answer is rather subjective. Mathematically the limit of a very low aspect ratio is a 2D airfoil moving through unconstrained medium. How high an AR can go is mainly dictated by structural soundness of the wing. For real aircraft, have a look at the classic example of a low aspect ratio wing - F-104. Typical high aspect ratio aircraft are most gliders. I would point you to the exceptionally interesting read that is Theory of wing Sections by Abbott and Doenhoff and also any book on aerodynamics, e.g. Anderson