Airfoil Data
NACA0006
NACA 0006
Wing Geometry Simulator
The NACA 0006 is a thin 3.0% chord-thickness airfoil with a maximum camber of 1.5% at 30% 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 -1.5°.
Thin airfoil theory predicts a stall angle near 12.1° and a peak lift-to-drag ratio around 44 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 NACA0006 appears in the wing design of at least 2 documented aircraft, including designs from Barlow/Brown and Agusta-Bell. Its proven track record across conventional and rotorcraft designs makes it one of the more field-validated profiles in the UIUC database.
Designers evaluating the NACA0006 typically compare it against profiles of similar thickness: NASA SC(2)-0706 AIRFOIL, NASA SC(2)-0606 AIRFOIL, NASA SC(2)-1006 AIRFOIL, NACA 16-006, EPPLER EA 8(-1)-006 AIRFOIL. The NACA 0024 is another reference profile frequently considered alongside it.
Aircraft Using the NACA0006 Airfoil
Barlow/Brown Turner Special | Barlow/Brown | NACA 0015 | NACA 0006 |
Agusta-Bell 212 | Agusta-Bell | NACA 0012 | NACA 0006 |
Wing lofting: 2 of these aircraft taper from NACA0006 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 NACA0006 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (3.0%) and max camber (1.5%).