Does distributed propulsion create unwanted lift at cruise speeds, requiring a negative angle of attack? Does distributed propulsion create unwanted lift at cruise speeds?

The great thing about slats and slotted flaps is that you can "turn them on" when you need high lift at takeoff, and "turn them off" when you don't need high lift during cruise.

So what about distributed propulsion by using 4 engines with props covering the majority of the wingspan? You can't turn off the extra lift off if you're trying to cruise as fast as possible.

I understand distributed propulsion adds a clmax of about 3.

Typically, you only need a Cl of 0.5 during cruise, but most GA planes cruise at about 75% power, almost at full power as on takeoff, so wouldn't a cl total of say 1-2 be generated with distributed propulsion?  That's 200 to 400% higher lift than needed.

To get rid of this extra lift and drag, wouldn't you need to lower the nose until the wings produce a " negative induced cl" of about -.5 to -1.5, adding the "distributed propulsion cl" of 1-2, for a total desired cL of about 0.5?

Is this correct, at least conceptually? Or does lift due to distributed propulsion trend to zero at a zero AOA? i.e. it's just additive if the wing is producing lift above a zero AOA
The fundamental way distributed propulsion adds extra lift is by blowing additional air over the wings. This is a direct thrust-to-lift conversion.

If you produce less thrust, you produce less lift with this arrangement. 

So, no, you don't go to a negative AoA to counteract the excess lift produced by running all of your motors at full power. You never produce that excess lift in the first place. This involves running your wing propulsors at reduced power, and if you have lift-assist propulsors, such as blown flaps, turning them off altogether.