Airfoil Data
FX68H120

The FX 68-H-120 is a 8.2% chord-thickness airfoil with a maximum camber of 4.1% at 28% 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 -4.1°.

Thin airfoil theory predicts a stall angle near 11.8° and a peak lift-to-drag ratio around 58 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The slim profile minimises pressure drag at higher speeds but leaves limited spar depth for structural integration.

Designers evaluating the FX68H120 typically compare it against profiles of similar thickness: E220 (11.48%), Zv(15-35)16, NASA/LANGLEY RC-12(B)3 AIRFOIL, AG36, SA7026. The GOE 101 AIRFOIL is another reference profile frequently considered alongside it.