Airfoil Data
N63012A
NACA 63012A AIRFOIL
Wing Geometry Simulator
The NACA 63012A AIRFOIL is a thin 6.0% chord-thickness airfoil with a maximum camber of 3.0% at 35% 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 N63012A appears in the wing design of at least 2 documented aircraft, including designs from Douglas and Dyke. Its proven track record across canard designs makes it one of the more field-validated profiles in the UIUC database.
Designers evaluating the N63012A typically compare it against profiles of similar thickness: SD8000-089-88, WORTMANN FX 71-120 AIRFOIL, NACA 64-012A AIRFOIL, NACA 16-012, NACA 0012-64. The NASA/LANGLEY 64-012 AIRFOIL is another reference profile frequently considered alongside it.
Aircraft Using the N63012A Airfoil
Douglas D-558-II Skyrocket | Douglas | NACA 63-010 | NACA 63-012 |
Dyke JD-2 Delta | Dyke | NACA 63-012 | NACA 66-015 |
Wing lofting: 2 of these aircraft taper from N63012A 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 N63012A 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%).