It seems more intuitive that drag would still increase as angle of attack is increased due to pressure drag and an effective increase in parasite area.
Yes. If you have a look at the drag polars of aerofoils (rather than finite wings), you still see a roughly quadratic dependence on lift coefficient (i.e. on AoA). For cambered wings, the minimum drag is not at zero lift coefficient. But that's not
induced drag.
but since you ask if the span is infinite the wing area is also infinite so CL can be 1/infinity
I started off thinking along the same lines, but actually you can imagine reducing the chord as you increase the span such that the wing area remains constant. You're flying a very long, narrow plank. In that case the AoA does indeed have to increase at low speed.