Airfoil Data
NACA643218

The NACA 64(3)-218 is a 10.0% chord-thickness airfoil with a maximum camber of 5.0% at 40% chord, suited to general-aviation and UAV wing design. At zero angle of attack the cambered geometry generates positive lift, giving an estimated zero-lift angle of -5.0°.

Thin airfoil theory predicts a stall angle near 11.7° and a peak lift-to-drag ratio around 63 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 10% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.

Designers evaluating the NACA643218 typically compare it against profiles of similar thickness: GOE 81 AIRFOIL, NACA 63(3)-218, MARSKE XM-1D AIRFOIL (F14-3.0), MH 81 13%, WORTMANN FX 79-K-144/17 AIRFOIL. The NACA 64-206 is another reference profile frequently considered alongside it.