Airfoil Data
NACA64206
NACA 64-206
Wing Geometry Simulator
The NACA 64-206 is a thin 4.1% chord-thickness airfoil with a maximum camber of 2.0% at 40% 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 -2.0°.
Thin airfoil theory predicts a stall angle near 12.0° and a peak lift-to-drag ratio around 47 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 NACA64206 appears in the wing design of at least 1 documented aircraft — notably by Bell. Its proven track record across canard designs makes it one of the more field-validated profiles in the UIUC database.
Designers evaluating the NACA64206 typically compare it against profiles of similar thickness: HQ 0/9 AIRFOIL, NACA 65-206, NACA 63-206, NACA 66-206, LWK 80-080. The NACA M11 AIRFOIL is another reference profile frequently considered alongside it.
Aircraft Using the NACA64206 Airfoil
Bell X-16 | Bell | NACA 64-210.5 | NACA 64-206 |
Wing lofting: 1 of these aircraft taper from NACA64206 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 NACA64206 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (4.1%) and max camber (2.0%).