Airfoil Data
N64012

The NASA/LANGLEY 64-012 AIRFOIL is a thin 6.0% chord-thickness airfoil with a maximum camber of 3.0% at 40% chord, suited to high-speed UAVs, sailplane tip sections, and propeller blade design. At zero angle of attack the cambered geometry generates positive lift, giving an estimated zero-lift angle of -3.0°.

Thin airfoil theory predicts a stall angle near 11.9° and a peak lift-to-drag ratio around 52 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The slim profile minimises pressure drag at higher speeds but leaves limited spar depth for structural integration.

The N64012 appears in the wing design of at least 1 documented aircraft — notably by Fukuda. Its proven track record across canard designs makes it one of the more field-validated profiles in the UIUC database.

Designers evaluating the N64012 typically compare it against profiles of similar thickness: EPPLER 428 AIRFOIL, GIII BL45 AIRFOIL, MH 43 8.5%, NASA/LANGLEY RC10-64C AIRFOIL, AG25 Bubble Dancer DLG by Mark Drela | The AG2x airfoils are intended to be used on composite versions of the Bubble Dancer and the Allegro-Lite.. The NACA M14 AIRFOIL is another reference profile frequently considered alongside it.