Airfoil Data
NACA663218

The NACA 66(3)-218 is a 10.1% chord-thickness airfoil with a maximum camber of 5.0% at 45% 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 64 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 NACA663218 typically compare it against profiles of similar thickness: GOE 685 AIRFOIL, AH 63-K-127/24, Smoothed ATR airfoil coordinates obtained using AFSMO (Harry Morgan's NASA smoothing program), FX 84-W-127, AH 93-K-130/15. The NACA 63(4)-221 is another reference profile frequently considered alongside it.