Airfoil Data
NACA64208
NACA 64-208
Wing Geometry Simulator
The NACA 64-208 is a thin 5.1% chord-thickness airfoil with a maximum camber of 2.5% 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 -2.5°.
Thin airfoil theory predicts a stall angle near 11.9° and a peak lift-to-drag ratio around 50 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 NACA64208 appears in the wing design of at least 4 documented aircraft, including designs from Airborne and Alpla-Werke. Its proven track record across canard designs makes it one of the more field-validated profiles in the UIUC database.
Designers evaluating the NACA64208 typically compare it against profiles of similar thickness: BOEING 707 .08 SPAN AIRFOIL, SD8020-010-88, EPPLER E850 AIRFOIL, NASA/LANGLEY RC-08(B)3 AIRFOIL, FX 79-L-100. The NACA 64-206 is another reference profile frequently considered alongside it.
Aircraft Using the NACA64208 Airfoil
Airborne Innovations Wizard | Airborne | NACA 64-??? | Constant |
Alpla-Werke AVo 68 Samburo | Alpla-Werke | Goettingen 549 | NACA 64-??? |
Hindustan Aeronautics Ltd HJT-36 Yashas | Hindustan | NACA 64-???? | Constant |
Siren C.30S Edelweiss | Siren | NACA 64-??? mod | Constant |
Wing lofting: 1 of these aircraft taper from NACA64208 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 NACA64208 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (5.1%) and max camber (2.5%).