I've heard two arguments about the canard wing configuration for this sort of purpose:
1. A canard config. will allow the canard wing to act as a stabilizer for the aircraft while adding to the net lift of the aircraft (vs. standard configuration stabilizers which work using negative lift)
2. for a canard wing configuration, the canard will stall first at a certain aircraft pitch angle; therefore, the maximum lift out of the main wing will not be attained because the canard wing reaches Clmax at its stall, then the aircraft pitches down again. (whereas in a tail-last configuration, the main wing stalls first allowing Clmax for the main wing to be achieved)
i think the first argument sounds fishy, but i just want to know if anybody has any key points to add. i'm a bit confused as to the usage of a canard wing configuration for maximum lift purposes.