Net drag reduction of 8 % (?) could be achieved. NLF airfoil was redesigned to have a longer laminar section and the aft flow was recovered by using small vortex generators at 75% or 85% chord position.
Some explaining pictures follow. The full text is in AIAA-2003-0211 "Enhanced Airfoil Design Incorporating Boundary Layer Mixing Devices".
Y-axis is the section lif coefficient cl and X-axis is the drag coefficient cd.
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