Airfoil Data
S1210

The S1210 12% is a 12.1% chord-thickness airfoil with a maximum camber of 6.0% at 34% 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 -6.0°.

Thin airfoil theory predicts a stall angle near 11.6° 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 S1210 typically compare it against profiles of similar thickness: WORTMANN FX 05-191 AIRFOIL, EPPLER 399 AIRFOIL, GOE 621 AIRFOIL, GOE 612 AIRFOIL, NACA 63(3)-618. The SC(2)-0714 | Supercritical airfoil (coordinates from Raymer w/ one correction). These coordinates are actual model coordinates, not coordinates as designed. Ref: NASA TP-2890 is another reference profile frequently considered alongside it.