Two-dimensional wind-tunnel investigation of an NACA 64-009 airfoil equipped with two types of leading-edge flap

Felicien F. Fullmer, Jr
naca-tn-1624
Jun 1948


An investigation was made to determine the effect of leading-edge flaps on the maximum lift coefficient of an NACA 64-009 airfoil and to compare the results with data obtained from previous tests as described in a previous NACA TN 1277.

An Adobe Acrobat (PDF) file of the entire report:
http://naca.central.cranfield.ac.uk/reports/1948/naca-tn-1624.pdf