Airfoil Data
FX74CL6140

The FX 74-CL6-140 is a 14.1% chord-thickness airfoil with a maximum camber of 7.1% at 34% 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 -7.1°.

Thin airfoil theory predicts a stall angle near 10.9° and a peak lift-to-drag ratio around 72 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.

Designers evaluating the FX74CL6140 typically compare it against profiles of similar thickness: FX 84-W-218, GW 25, GOE 504 AIRFOIL, Rhode St. Genese 34, GOE 289 (MVA 289) AIRFOIL. The FX74_CL5_140 is another reference profile frequently considered alongside it.