Airfoil Data
FX66S161
FX 66-S-161 AIRFOIL
Wing Geometry Simulator
The FX 66-S-161 AIRFOIL is a 11.9% chord-thickness airfoil with a maximum camber of 5.9% 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 -5.9°.
Thin airfoil theory predicts a stall angle near 11.6° and a peak lift-to-drag ratio around 69 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 12% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.
The FX66S161 appears in the wing design of at least 1 documented aircraft — notably by Kortenbach. Its proven track record across rotorcraft designs makes it one of the more field-validated profiles in the UIUC database.
Designers evaluating the FX66S161 typically compare it against profiles of similar thickness: NACA 2-H-15 AIRFOIL, RAF 69 AIRFOIL, EPPLER 1200 AIRFOIL, EPPLER 266 AIRFOIL, FX S 03-182 AIRFOIL. The FX 66-H-60 is another reference profile frequently considered alongside it.
Aircraft Using the FX66S161 Airfoil
Kortenbach & Rauh Kora I | Kortenbach | Wortmann FX 66-S-196 | Wortmann FX 66-S-161 |
Wing lofting: 1 of these aircraft taper from FX66S161 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 FX66S161 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (11.9%) and max camber (5.9%).