Airfoil Data
N63210
NACA 63-210 AIRFOIL
Wing Geometry Simulator
The NACA 63-210 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 N63210 appears in the wing design of at least 3 documented aircraft, including designs from Heuberger and Composites. Its proven track record across canard designs makes it one of the more field-validated profiles in the UIUC database.
Designers evaluating the N63210 typically compare it against profiles of similar thickness: LWK 80-120/K25, HAWKER TEMPEST 96.77% SEMISPAN AIRFOIL, FX 79-L-120, DS21 Joe Wurts, FX 76-120. The NACA 64A-010 10.0% is another reference profile frequently considered alongside it.
Aircraft Using the N63210 Airfoil
Composites Engineering BQM-167 Skeeter | Composites | NACA 63-210 | NACA 63-206 |
Heuberger Sizzler | Heuberger | NACA 63-210 | Constant |
Heuberger Stinger | Heuberger | NACA 63-210 | Constant |
Wing lofting: 1 of these aircraft taper from N63210 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 N63210 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%).