Airfoil Data
FX66196V
FX 66-S-196 V1 AIRFOIL
Wing Geometry Simulator
The FX 66-S-196 V1 AIRFOIL is a 13.7% chord-thickness airfoil with a maximum camber of 6.8% at 40% 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 -6.8°.
Thin airfoil theory predicts a stall angle near 11.0° and a peak lift-to-drag ratio around 71 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.
The FX66196V appears in the wing design of at least 2 documented aircraft — notably by Schempp-Hirth. Its proven track record across canard designs makes it one of the more field-validated profiles in the UIUC database.
Designers evaluating the FX66196V typically compare it against profiles of similar thickness: RONCZ R1145MS AIRFOIL, RONCZ R1145MS MAIN ELEMENT, GOE 630 AIRFOIL, GOE 234 (MVA CA5) AIRFOIL, GOE 288 AIRFOIL. The FX 66-S-161 AIRFOIL is another reference profile frequently considered alongside it.
Aircraft Using the FX66196V Airfoil
Schempp-Hirth Cirrus | Schempp-Hirth | Wortmann FX 66-196 | Wortmann FX 66-161 |
Schempp-Hirth Cirrus B | Schempp-Hirth | Wortmann FX 66-196 | Wortmann FX 60-161 |
Wing lofting: 2 of these aircraft taper from FX66196V 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 FX66196V frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (13.7%) and max camber (6.8%).