Airfoil Data
FX67K170

The FX 67-K-170/17 AIRFOIL is a 13.6% chord-thickness airfoil with a maximum camber of 6.8% at 43% 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 -6.8°.

Thin airfoil theory predicts a stall angle near 11.1° and a peak lift-to-drag ratio around 71 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 14% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.

The FX67K170 appears in the wing design of at least 65 documented aircraft, including designs from Caproni and Glasflugel. 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 FX67K170 typically compare it against profiles of similar thickness: FX 66-S-196 AIRFOIL, GOE 8K AIRFOIL, St. CYR 24 (Bartel 35-IIIC), NACA 23024, EPPLER 748 AIRFOIL. The RONCZ 1080 VOYAGER INNER AFT WING AIRFOIL is another reference profile frequently considered alongside it.