Airfoil Data
NACA63206
NACA 63-206
Wing Geometry Simulator
The NACA 63-206 is a thin 4.0% 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 NACA63206 appears in the wing design of at least 2 documented aircraft, including designs from Composites and Dean. Its proven track record across canard designs makes it one of the more field-validated profiles in the UIUC database.
Designers evaluating the NACA63206 typically compare it against profiles of similar thickness: LWK 80-080, NACA M2, HQ 0/9 AIRFOIL, FX 77-080, NACA 64-206. The NACA M14 AIRFOIL is another reference profile frequently considered alongside it.
Aircraft Using the NACA63206 Airfoil
Composites Engineering BQM-167 Skeeter | Composites | NACA 63-210 | NACA 63-206 |
Dean Delt-Air 250 | Dean | NACA 63-206 mod | Constant |
Wing lofting: 1 of these aircraft taper from NACA63206 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 NACA63206 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (4.0%) and max camber (2.0%).