# Would plain and slotted flaps increase lift substantially in a distributed propulsion application?

Would plain and slotted flaps increase lift substantially in a distributed propulsion application for a slow moving aircraft (15mph)?

I understand that:

1. A classic NACA foil without flaps such as the NACA 650-18, as used on Zenith 701 STOL aircraft produces a maximum lift coefficient (Clmax) of approx. 1.5.

2. Add a plain non-slotted flap, and the Clmax increases to roughly 2.2.

3. Add slotted flaps, and the Clmax increases to roughly 2.8.

4. The maximum Clmax of distributed propulsion is 12.

5. Given a GA aircraft such as the Zenith 701, with an engine of 100HP, with a stall speed of 45mph, means the entire wing is bathed in air travelling at 45mph when flying at 45mph.

6. Assume the same given aircraft now has multiple propellers installed along it's entire leading edge in a distributed propulsion arrangement, with multiple engines totalling the same total Hp, flying at roughly 15mph and with an propeller exit speed of 45mph. This also means the entire wing is bathed in air travelling at 45mph. ( assume 100% efficiency, no swirl angle, etc.).

See graph below. (Solid black graph - Source: Aviationchief.com. Added graphics estimated by the OP.)

1. As distributed propulsion is just "extra air", and flaps move the lift slope curve up and to the left, I would think the wing would see substantial increase in Clmax if plain flaps or slotted flaps added.

2. I understand that in distributed propulsion, a wing with a Clmax of 6, on a slow flying aircraft, (15mph), but prop exit speed 300% faster at 45mph, the local AoA would always be under 10 deg.

3. I would think there would be a substantial increase in lift when using a plain flap and even more when using a slotted flap, but almost no increase in Clmax above 10 deg AOA.

Is this correct thinking?