Airfoil Data
NACA001264
NACA 0012-64
Wing Geometry Simulator
The NACA 0012-64 is a thin 6.0% chord-thickness airfoil with a maximum camber of 3.0% 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 -3.0°.
Thin airfoil theory predicts a stall angle near 11.9° and a peak lift-to-drag ratio around 52 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 NACA001264 appears in the wing design of at least 1 documented aircraft — notably by Rockwell. Its proven track record across rotorcraft designs makes it one of the more field-validated profiles in the UIUC database.
Designers evaluating the NACA001264 typically compare it against profiles of similar thickness: NACA 16-012, E. Bambino, NASA SC(2)-0012 AIRFOIL, NACA 0012-34, J5012 12%. The LOCKHEED L-188 TIP AIRFOIL is another reference profile frequently considered alongside it.
Aircraft Using the NACA001264 Airfoil
Rockwell Space Shuttle Orbiter | Rockwell | NACA 0010 mod | NACA 0012-64 mod |
Wing lofting: 1 of these aircraft taper from NACA001264 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 NACA001264 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (6.0%) and max camber (3.0%).