Airfoil Data
FX6617A2

The FX 66-17AII-182 AIRFOIL is a 12.9% chord-thickness airfoil with a maximum camber of 6.4% at 37% 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 -6.4°.

Thin airfoil theory predicts a stall angle near 11.3° 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 FX6617A2 typically compare it against profiles of similar thickness: FX 66-182 AIRFOIL, USA 98 AIRFOIL, GOE 683 AIRFOIL, EPPLER 656 AIRFOIL, WORTMANN FX 66-17A-175 AIRFOIL. The WORTMANN FX 66-17AII-182 AIRFOIL (AS TESTED AT NASA) is another reference profile frequently considered alongside it.