Investigation of boundary-layer Reynolds number for transition on an NACA 65(215)-114 airfoil in the Langley two-dimensional low-turbulence pressure tunnel

Albert L. Braslow, Fioravante Visconti
naca-tn-1704
Oct 1948


A low-turbulence wind-tunnel investigation was made of an aerodynamically smooth NACA 65(215)-114 airfoil having faired surfaces back to 37 percent chord to determine the magnitude of the boundary-layer Reynolds number at various positions of transition from laminar to turbulent flow along both airfoil surfaces.

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http://naca.central.cranfield.ac.uk/reports/1948/naca-tn-1704.pdf