An investigation of the section characteristics of plain unsealed ailerons on an NACA 66,1-115 airfoil section in the Langley 8-foot high-speed tunnel

Arvo A. Luoma
naca-tn-1596
Jan 1949


Complete pressure-distribution measurements were made over a 24-inch-chord NACA 66,1-115 airfoil section equipped with unsealed 20-percent-chord plain ailerons of true-airfoil-contour profile and 30 degree beveled-trailing-edge profile. The model was tested with aerodynamically smooth surfaces.

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http://naca.central.cranfield.ac.uk/reports/1949/naca-tn-1596.pdf