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

Felicien F. Fullmer, Jr
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.

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