Airfoil Data
S1020

The S1020 Ornithopter airfoil is a 12.2% chord-thickness airfoil with a maximum camber of 6.1% at 38% 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 S1020 typically compare it against profiles of similar thickness: GOE 645 AIRFOIL, GOE 476 AIRFOIL, GOE 611 AIRFOIL, GOE 528 AIRFOIL, NACA 65(3)-618. The NACA 1412 is another reference profile frequently considered alongside it.