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
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.

An Adobe Acrobat (PDF) file of the entire report: