Airfoil Data
FX6617AI

The WORTMANN FX 66-17AII-182 AIRFOIL (AS TESTED AT NASA) is a 13.1% chord-thickness airfoil with a maximum camber of 6.5% at 35% 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 -6.5°.

Thin airfoil theory predicts a stall angle near 11.2° and a peak lift-to-drag ratio around 70 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 13% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.

Designers evaluating the FX6617AI typically compare it against profiles of similar thickness: GOE 225 (MVA H.35) AIRFOIL, GOE 692 AIRFOIL, EPPLER 856 AIRFOIL, GOE 646 AIRFOIL, GOE 675 AIRFOIL. The FX 66-17AII-182 AIRFOIL is another reference profile frequently considered alongside it.