Airfoil Data
FX63137

The WORTMANN FX 63-137 AIRFOIL is a 12.2% chord-thickness airfoil with a maximum camber of 6.1% 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 -6.1°.

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.

The FX63137 appears in the wing design of at least 31 documented aircraft, including designs from Diamond and Hoffman. Its proven track record across conventional and rotorcraft designs makes it one of the more field-validated profiles in the UIUC database.

Designers evaluating the FX63137 typically compare it against profiles of similar thickness: GOE 615 AIRFOIL, FX 63-137 13.7% smoothed, GOE 464 AIRFOIL, NACA 65(3)-618, NACA 64(3)-618. The PROPFAN CRUISE MISSILE WING AIRFOIL is another reference profile frequently considered alongside it.