Airfoil Data
FX61168

The FX 61-168 AIRFOIL is a 11.4% chord-thickness airfoil with a maximum camber of 5.7% at 37% chord, suited to general-aviation and UAV wing design. At zero angle of attack the cambered geometry generates positive lift, giving an estimated zero-lift angle of -5.7°.

Thin airfoil theory predicts a stall angle near 11.6° and a peak lift-to-drag ratio around 67 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 11% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.

The FX61168 appears in the wing design of at least 13 documented aircraft, including designs from Szybowcowy and Birmingham. 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 FX61168 typically compare it against profiles of similar thickness: AH 79-100 C AIRFOIL, GOE 301 (FRIEDRICHSHAFEN G 13) AIRFOIL, GOE 406 AIRFOIL, USA 45 AIRFOIL, NACA M25 AIRFOIL. The MI-STRUT1 is another reference profile frequently considered alongside it.