Airfoil Data
FX60126
WORTMANN FX 60-126 AIRFOIL
Wing Geometry Simulator
The WORTMANN FX 60-126 AIRFOIL is a 9.2% chord-thickness airfoil with a maximum camber of 4.6% at 34% 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 -4.6°.
Thin airfoil theory predicts a stall angle near 11.7° and a peak lift-to-drag ratio around 61 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.
The FX60126 appears in the wing design of at least 86 documented aircraft, including designs from Schleicher and Akaflieg. 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 FX60126 typically compare it against profiles of similar thickness: EPPLER 67 AIRFOIL, CLARK Y AIRFOIL, GOE 184 (MVA H.29) AIRFOIL, GOE 804 (EA 8) AIRFOIL, Davis AIRFOIL. The GOE 630 AIRFOIL is another reference profile frequently considered alongside it.
Aircraft Using the FX60126 Airfoil
Wing lofting: 84 of these aircraft taper from FX60126 at the root to a different tip section. Use the Tapered filter to isolate them, then click any tip airfoil link to compare geometries.
Related Airfoils
Engineers evaluating the FX60126 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (9.2%) and max camber (4.6%).