Airfoil Data
NACA653618

The NACA 65(3)-618 is a 12.2% chord-thickness airfoil with a maximum camber of 6.1% at 40% chord, suited to high-lift UAV wings, RC sailplanes, and low-Reynolds-number slow-flyers. At zero angle of attack the cambered geometry generates positive lift, giving an estimated zero-lift angle of -6.1°.

Thin airfoil theory predicts a stall angle near 11.5° and a peak lift-to-drag ratio around 69 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 12% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.

Designers evaluating the NACA653618 typically compare it against profiles of similar thickness: GOE 464 AIRFOIL, GOE 645 AIRFOIL, WORTMANN FX 63-137 AIRFOIL, S1020 Ornithopter airfoil, GOE 615 AIRFOIL. The NACA 5-H-20 AIRFOIL is another reference profile frequently considered alongside it.