Airfoil Data
NACA2411

The NACA 2.5411 is a thin 7.9% chord-thickness airfoil with a maximum camber of 4.0% at 34% chord, suited to high-speed UAVs, sailplane tip sections, and propeller blade design. At zero angle of attack the cambered geometry generates positive lift, giving an estimated zero-lift angle of -4.0°.

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.

The NACA2411 appears in the wing design of at least 12 documented aircraft — notably by Industrie. Its proven track record across canard designs makes it one of the more field-validated profiles in the UIUC database.

Designers evaluating the NACA2411 typically compare it against profiles of similar thickness: HOBIE, SELIG 3002-099-83, WORTMANN FX 082-512 AIRFOIL, KC-135 BL124.32 AIRFOIL, ARA-D 6% AIRFOIL. The NACA 2412 is another reference profile frequently considered alongside it.