An experimental investigation of the NACA 631-012 airfoil section with leading-edge and midchord suction slots

George B. McCullough, Donald E. Gault
naca-tn-2041
Feb 1950


A previous investigation of boundary-layer control employing a two-dimensional model of the NACA 631-012 airfoil section demonstrated the ability of a single suction alot near the leading edge to increase maximum lift. It was believed possible, however, that the complete stall may have resulted from leading-edge separation because of the inability of the nose suction to hold the flow on the surface.

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http://naca.central.cranfield.ac.uk/reports/1950/naca-tn-2041.pdf