Airfoil Data
NACA663418

The NACA 66(3)-418 is a 11.2% chord-thickness airfoil with a maximum camber of 5.6% 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 -5.6°.

Thin airfoil theory predicts a stall angle near 11.6° and a peak lift-to-drag ratio around 67 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 11% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.

Designers evaluating the NACA663418 typically compare it against profiles of similar thickness: EPPLER STF 863-615 AIRFOIL, DEFIANT CANARD BL110 AIRFOIL, GOE 29B AIRFOIL, EPPLER 343 AIRFOIL, FX 63-145 AIRFOIL. The NACA M4 AIRFOIL is another reference profile frequently considered alongside it.