Experimental investigation of an NACA 64A010 airfoil section with 41 suction slots on each surface for control of laminar boundary layer

Dale L. Burrows, Milton A. Schwartzberg
naca-tn-2644
Apr 1952


An investigation has been made of boundary-layer suction through flush surface slots as a means for increasing the extent of laminar flow on the NACA 64A010 airfoil section. The 3-foot-chord model was designed according to an analysis presented herein to maintain nearly full-chord laminar flow at Reynolds numbers up to 25 X 10(exp 6) with the use of 41 suction slots on each surface.

An Adobe Acrobat (PDF) file of the entire report:
http://naca.central.cranfield.ac.uk/reports/1952/naca-tn-2644.pdf